Wing-shaped structure suitable for ice prevention and deicing

Abstract

The invention relates to the technical field of aviation equipment, and discloses a wing-shaped structure suitable for anti-icing and deicing, which comprises a shell and an electric heating piece, an electric heating piece is arranged in a shell, a first heating layer is formed on the upper wing face and the lower wing face of the inner wall of the shell, a second heating layer is formed on the front edge of the inner wall of the shell, the first heating layer and the second heating layer are electrically connected, and the first heating layer and the second heating layer are connected with an external power source through an electrode layer so that power can be supplied to the electric heating piece, and temperature distribution of different parts can be controlled. After the electrode layer conducts electricity, a first temperature area is formed on the first heating layer, a second temperature area is formed on the second heating layer, and the temperature of the first temperature area is lower than that of the second temperature area, so that it is guaranteed that the front edge of the airfoil structure is kept at the high temperature, and the deicing and anti-icing requirements are met. According to the airfoil structure suitable for anti-icing and deicing, differentiated heating can be conducted according to icing characteristics of different parts of the airfoil structure, it is guaranteed that the anti-icing and deicing requirements are met, meanwhile, energy consumption is reduced, and the energy utilization rate is increased.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aviation equipment, in particular to a wing profile structure suitable for ice prevention and removal. BACKGROUND

[0002] The wing is an important aerodynamic component of an airplane, and the design and performance optimization thereof directly affect the airplane control, fuel efficiency and flight safety. However, when the airplane flies in an icing prone airspace, the low temperature environment causes the wing to be prone to icing, which affects the aerodynamic characteristics and flight dynamics characteristics of the airplane, and may even lead to flight loss of control. Therefore, solving the wing icing problem has great significance for improving the airplane controllability and ensuring the safe flight of the airplane.

[0003] At present, most wing ice prevention and removal systems are designed to increase the temperature of the wing leading edge wall by using engine bleed air, so as to achieve the purpose of ice prevention and removal. Although this method is reliable and effective, the structure design is complex, and the engine thrust is also lost to some extent during the engine bleed air ice removal process, and the energy consumption is high.

[0004] In addition, the commonly used ice prevention and removal technology is the electric heating technology, which converts electric energy into heat energy by Joule heating, and the heat generated increases the temperature of the wing surface, thereby achieving the effect of ice prevention and removal. The traditional electric heating ice prevention and removal system generally uses resistance wires and conductive films as heating elements, and the heat conduction uniformity and conformality thereof are poor. In the actual wing ice prevention and removal process, the wing leading edge usually needs a higher ice removal temperature, and both the bleed air ice prevention and removal technology and the electric heating ice prevention and removal technology need to set the overall temperature high enough, which leads to the generation of excess heat on the upper and lower wing surfaces, resulting in increased energy consumption and low energy utilization rate. SUMMARY

[0005] Therefore, the present application provides a wing profile structure suitable for ice prevention and removal, so as to solve the problem that the wing profile structure in the prior art cannot form different temperature zones on the same material to meet the ice prevention and removal requirements of different parts, and the energy consumption is large and the utilization rate is low.

[0006] To solve the above technical problems, the technical scheme of the present application is as follows: The present application provides a wing profile structure suitable for ice prevention and removal, comprising: a shell and an electric heating element; the electric heating element is arranged inside the shell, and a first heating layer is formed on the upper wing surface and the lower wing surface 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 the outer side of the first heating layer is provided with an electrode layer; the electrode layer is connected with an external power supply to supply power to the electric heating element, so that the first heating layer has a first temperature zone, the second heating layer has a second temperature zone, and the temperature of the first temperature zone is lower than that of the second temperature zone.

[0007] It has the following advantages: The present invention provides an airfoil structure suitable for anti-icing and de-icing. By arranging an electric heating element inside the shell, and forming a first heating layer on the upper and lower wing surfaces of the inner wall of the shell, respectively, and forming a second heating layer on the leading edge, the first heating layer and the second heating layer are electrically connected, and connected to an external power supply through an electrode layer, it is possible to supply power to the electric heating element and control the temperature distribution of different parts. After the electrode layer is 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 that 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 de-icing and anti-icing requirements. The present invention provides an airfoil structure suitable for anti-icing and de-icing. It can perform differential heating according to the icing characteristics of different parts of the airfoil structure, while ensuring that the anti-icing and de-icing requirements are met, reducing energy consumption and improving energy utilization.

[0008] According to some embodiments of the present invention, the first heating layer is formed by weaving a first fiber monomer, and the first fiber monomer includes a fiber monofilament, a graphene layer and a first metal layer from the inside to the outside in the radial direction; or the first fiber monomer includes a fiber monofilament, a graphene layer and a metal compound layer in sequence from the inside to the outside.

[0009] According to some embodiments of the present invention, the second heating layer is formed by weaving second fiber monomers, and the second fiber monomers include fiber monofilaments and graphene layers from the inside to the outside in the radial direction.

[0010] According to some embodiments of the present invention, the first metal layer or the metal compound layer is composited on the graphene layer of the second heating layer by evaporation to obtain the first heating layer; the first metal layer is copper, tin, bismuth or iron, and the metal compound layer is bismuth trioxide.

[0011] 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.

[0012] 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.

[0013] According to some embodiments of the present invention, the first temperature zone and the second temperature zone have the same temperature rise response speed.

[0014] According to some embodiments of the present invention, the first temperature zone and the second temperature zone have the same temperature drop response speed.

[0015] 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.

[0016] According to some embodiments of the present invention, the shell includes a surface coating, a thermal conductive layer and an insulating layer arranged in sequence from the outside of the shell toward the electric heating element, and an insulating layer, a thermal conductive layer and a surface coating arranged in sequence from the electric heating element toward the inside of the shell. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 A schematic diagram of an airfoil structure suitable for anti-icing and de-icing provided in some embodiments of the present invention; Figure 2 A planar expansion schematic diagram of an electric heating element provided in some embodiments of the present invention; Figure 3 A schematic cross-sectional view of a first fiber monomer of a first heating layer provided in some embodiments of the present invention; Figure 4 A schematic diagram of a cross-sectional plane expansion of an electrode layer attached to a second fiber monomer provided in some embodiments of the present invention; Figure 5 A schematic diagram of a planar expansion of a cross section of a second fiber monomer of a second heating layer provided in some embodiments of the present invention; Figure 6 A microscopic topography of the surface of the first heating layer provided in some embodiments of the present invention; Figure 7 A comparison diagram of the surface microscopic morphology of the first heating layer and the second heating layer provided in some embodiments of the present invention; Figure 8 This is an infrared radiation diagram of an electric heating element provided in some embodiments of the present invention at a working voltage of 45V; Figure 9 The time-temperature curve of the electric heating element provided in some embodiments of the present invention at a working voltage of 45V; Figure 10 It is the equivalent circuit diagram between the single fibers in a bundle of fibers; Figure 11 It is the equivalent circuit diagram of the warp fiber bundle and weft fiber bundle of the fiber fabric.

[0019] Description of reference numerals: 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 DESCRIPTION

[0020] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0021] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present 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.

[0022] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0023] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0024] 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 arranged inside the shell 1, and a first heating layer 21 is formed on the upper and lower airfoil 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 provided 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, so that the first heating layer 21 has a first temperature zone, the second heating layer 22 has a second temperature zone, and the temperature of the first temperature zone is lower than the temperature of the second temperature zone.

[0025] Specifically, the present invention provides an airfoil structure suitable for anti-icing and de-icing. By arranging an electric heating element 2 inside a shell 1, and forming a first heating layer 21 on the upper and lower wing surfaces of the inner wall of the shell 1, respectively, and forming a second heating layer 22 on the leading edge, the first heating layer 21 and the second heating layer 22 are electrically connected, and connected to an external power source through an electrode layer 23, so that power can be supplied to the electric heating element 2 and the temperature distribution of different parts can be controlled. After the electrode layer 23 is 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, thereby ensuring 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 the present invention can perform differential heating according to the icing characteristics of different parts of the airfoil structure, while ensuring that the requirements of anti-icing and de-icing are met, reducing energy consumption and improving energy utilization.

[0026] It can be understood that the setting of the electric heating element 2 enables multiple heating areas to be formed inside the same shell 1 material to form different temperature areas, thereby realizing differentiated de-icing requirements at different positions of the wing structure, and improving de-icing efficiency and targeting; different heating areas set corresponding temperatures according to actual anti-icing requirements to avoid overheating of non-critical areas, thereby effectively reducing overall energy consumption; the electric heating element 2 is uniformly connected to the external power supply through the electrode layer 23, the circuit structure is simple, the heat transfer path is short, and the energy transfer efficiency is high, which improves the overall energy utilization rate; the wing structure described in the present invention is suitable for a variety of operating environments, especially suitable for use in low temperature, high humidity and other icing-prone environments, and has broad application prospects.

[0027] Reference Figure 3 As shown, in some embodiments of the present invention, the first heating layer 21 is woven by a first fiber monomer, and the first fiber monomer includes a fiber monofilament 3, a graphene layer 4 and a first metal layer 5 from the inside to the outside in the radial direction; or the first fiber monomer includes a fiber monofilament 3, a graphene layer 4 and a metal compound layer in sequence from the inside to the outside.

[0028] Reference Figure 5 As shown, in some embodiments of the present invention, the second heating layer 22 is formed by weaving a second fiber monomer, and the first fiber monomer includes a fiber monofilament 3 and a graphene layer 4 from the inside to the outside in the radial direction.

[0029] In some embodiments of the present invention, the first metal layer 5 or the metal compound layer is composited on the graphene layer 4 of the second heating layer 22 by evaporation 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.

[0030] Specifically, in a specific embodiment of the present invention, the fiber filaments 3 and graphene layers 4 used in the first and second fiber monomers are made of the same material, and the graphene layers 4 have the same thickness. Several fiber filaments 3 are bound into a fiber tow, which is then woven into a fiber fabric. During the preparation process of the electric heater 2, a graphene layer 4 is uniformly deposited and grown on the fiber fabric to form the second heating layer 22. Based on the differentiated anti-icing requirements at different locations of the airfoil structure, a mold is used to shield the leading edge relative to the airfoil structure. The mold can be a high-temperature resistant quartz mold, leaving the portions opposite the upper and lower surfaces of the airfoil structure exposed. Subsequently, a metal or metal compound targeting material is deposited on the surface of the exposed second heating layer 22 by vacuum evaporation. The metal targeting material can be copper, tin, bismuth, or iron, and the metal compound targeting material can be bismuth trioxide, thereby forming the first heating layer 21 on the upper and lower surfaces of the airfoil structure.

[0031] It can be understood that in a specific embodiment of the present invention, the fiber monofilament 3 is glass fiber, and the average square resistance of the second heating layer 22 formed by the fiber monofilament 3 and the graphene layer 4 is 800Ω / sq; the material of the first metal layer 5 is copper, and the deposition thickness is 50nm.

[0032] Specifically, in Figures 6 to 9 In the figure, GGFF represents the second fiber monomer on which metal copper is not deposited, i.e., the second heating layer 22; GGFF-Cu represents the first fiber monomer on which metal copper is deposited, i.e., the first heating layer 21; GGFF-Cu1 and GGFF-Cu2 represent the first heating layers 21 located in two different areas in the electric heating element.

[0033] After depositing a 50nm copper metal layer on the first heating layer 21 with an average square resistance of 800Ω / sq, the surface morphologies of the first heating layer 21 and the second heating layer 22 are compared. Figure 6 and Figure 7 As shown. Figure 6 This is a microscopic morphology image 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 evenly coated on the glass fiber; Figure 7The surface morphology of the first heating layer 21 and the second heating layer 22 is compared. The images of the two areas under a scanning electron microscope only show a brightness difference caused by the difference in electrical conductivity. There is no gap between the single fibers, nor is there any pore between the warp and weft fiber bundles covered by the metal layer. This proves that the nano-scale first metal layer 5 is evenly coated on each fiber monomer. The gaps between the single fibers of the first heating layer 21 and the second heating layer 22, as well as the pores between the fiber bundles, still exist, and do not affect their original overall structure and flexibility. If a thicker first metal layer 5 is compounded through other processes, it may cause the interlayer interface strength to decrease after curing and forming, resulting in cracking. It may also affect resin penetration, resulting in local low resin content, affecting the strength of the structural component.

[0034] 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.

[0035] Specifically, an inorganic fiber fabric can be selected according to specific needs, and graphene can be deposited on the inorganic fiber fabric to form a second heating layer 22 with different square resistances. The average square 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.; further, a metal layer or a metal compound layer is deposited on the surface of the second heating layer 22 to obtain the 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 15nm, 30nm, 40nm, 50nm and 100nm can be selected.

[0036] 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, and the electrode layer 23 is distributed in a strip shape. The electrode layer 23 is a second metal layer. The electrode layer can be prepared by spraying, coating, screen printing, inkjet printing, etc. according to the conductivity requirements of the electrode, and the present invention is not specifically limited.

[0037] Specifically, 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 differentiated anti-icing requirements at different positions of the airfoil structure, a mold is used to shield the leading edge portion and the electrode portions on both sides relative to the airfoil structure. The mold can be a high-temperature resistant quartz mold so that the portions relative to the upper and lower surfaces of the airfoil structure are exposed. Subsequently, a metal or metal compound targeting material is deposited on the surface of the exposed second heating layer 22 by vacuum evaporation. 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 surfaces of the airfoil structure. The mold shielding is removed, and a second metal layer is covered on the surface of the second heating layer 22 at the electrode portions on both sides. The second metal layer is made of a conductive metal material to form an electrode layer 23. The specific conductive metal material can be copper or silver. The thickness of the electrode layer 23 is 40-80 μm. 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 demand.

[0038] In some embodiments of the present invention, the first temperature zone and the second temperature zone have the same temperature rise response speed.

[0039] In some embodiments of the present invention, the first temperature zone and the second temperature zone have the same temperature drop response speed.

[0040] Specifically, the fiber monofilament 3 is selected as glass fiber, the second heating layer 22 has an average square resistance of 800Ω / sq, and a 50nm first metal layer 5 is deposited on the second heating layer 22. The first metal layer 5 is made of copper to form a first heating layer 21. An AC voltage is applied to the electric heating element 2 using an adjustable voltage power supply. The surface temperature of the electric heating element 2 increases, and an infrared thermal imager is used to scan and record the radiated heat to observe the uniformity of its surface temperature.

[0041] Temperature indication Figure 8 As shown in the figure, there is a significant temperature difference between the saturation temperatures of the first heating layer 21 and the second heating layer 22, proving that the saturation temperature of the heating area can be effectively changed after the first metal layer 5 is deposited on the second heating layer 22 by vacuum evaporation. Continuously apply 45V AC voltage for 110s, cool for 90s, record the average temperature of the first heating layer 21 and the second heating layer 22, and obtain a surface temperature change curve over time, as shown in Figure 1. Figure 9. The temperatures of the first heating layer 21 and the second heating layer 22 both rose rapidly within 15 seconds and reached the saturation temperature within 40 seconds; among them, the saturation temperature of the second heating layer 22 was about 112°C, and the saturation temperature of the first heating layer 21 was about 92°C, with a temperature difference of about 20°C. After turning off the power, the surface temperature of the three areas of the electric heating element dropped rapidly, and dropped to the initial temperature after about 20 seconds. This shows that the deposition of the first metal layer 5 only changed the square resistance value, resulting in a temperature difference between the two areas after power was turned on; and it had no effect on the excellent electrical and thermal conductivity of the graphene glass fiber fabric, and the heating response speed and the cooling response speed remained basically unchanged.

[0042] The first heating layer 21 is obtained by depositing the first metal layer 5 on the surface of the second heating layer 22 by evaporation. 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 , the contact resistance R between the fiber monofilaments con1 and the contact resistance R between the warp fiber bundle and the weft fiber bundle con2 The resistance R1 and R2 between each fiber monofilament are in parallel relationship, and then the contact resistance R con1 In series, the total resistance of a bundle of fiber monomers is R x(y) Including the resistance R of each fiber n Contact resistance R between the fiber and the single fiber con1 , the equivalent circuit diagram is as follows Figure 10 As shown; Warp fiber bundle resistance R x and the weft fiber bundle resistance R y In parallel, then with the contact resistance R at the junction between the beams con2 In series, the equivalent circuit diagram is 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 con2 According to Ohm's law, the total resistance in a series circuit is equal to the sum of the individual resistances, so the contact resistance R between the fiber filaments is con1 The decrease in fiber bundle resistance R x(y) The contact resistance R con2 The reduction in the total resistance R decreases.

[0043] Therefore, the addition of the first metal layer 5 is equivalent to providing a conductive path between the fiber monofilaments and between the warp fiber bundles and the weft fiber bundles, thereby reducing the contact resistance, the total resistance R, and the square resistance.

[0044] According to some embodiments of the present application, the fiber filaments 3 are quartz fiber filaments, glass fiber filaments, ceramic fiber filaments, carbon fiber filaments, alumina fiber filaments or boron fiber filaments, and the fiber fabric woven by the fiber filaments can be a quartz fiber fabric, a glass fiber fabric, a ceramic fiber fabric, a carbon fiber fabric, an alumina fiber fabric or a boron fiber fabric.

[0045] According to some embodiments of the present application, the shell 1 comprises, in sequence from the outside of the shell towards the electric heating element 2, a surface coating layer, a heat conducting layer and an insulating layer, and, in sequence from the electric heating element 2 towards the inside of the shell, an insulating layer, a heat conducting layer and a surface coating layer.

[0046] Although the embodiments of the present application have been described in conjunction with the accompanying drawings, various modifications and changes can be made by those skilled in the art without departing from the spirit and scope of the present application, and such modifications and changes are intended to fall within the scope of the appended claims.

Claims

1. An airfoil structure suitable for anti-icing and de-icing, characterized in that: include: housing (1); An electric heating element (2) is arranged 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 provided 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), so that the first heating layer (21) has a first temperature zone, and the second heating layer (22) has a second temperature zone, and the temperature of the first temperature zone is lower than the temperature of the second temperature zone.

2. The airfoil structure suitable for anti-icing and de-icing according to claim 1, characterized in that: The first heating layer (21) is formed by weaving a first fiber monomer, wherein the first fiber monomer includes, radially from the inside to the outside, a fiber monofilament (3), a graphene layer (4), and a first metal layer (5); or the first fiber monomer includes, radially from the inside to the outside, a fiber monofilament (3), a graphene layer (4), and a metal compound layer.

3. The airfoil structure suitable for anti-icing and de-icing according to claim 2, characterized in that: The second heating layer (22) is formed by weaving second fiber monomers, and the second fiber monomers sequentially comprise fiber monofilaments (3) and graphene layers (4) from the inside to the outside in the radial direction.

4. The airfoil structure suitable for anti-icing and de-icing according to claim 3, characterized in that: The first metal layer (5) or the metal compound layer is composited on the graphene layer (4) of the second heating layer (22) by vapor deposition to obtain a first heating layer (21); the first metal layer (5) is copper, tin, bismuth or iron, and the metal compound layer is bismuth trioxide.

5. The airfoil structure suitable for anti-icing and de-icing according to claim 4, characterized in that: The thickness of the first metal layer (5) or the metal compound layer is less than or equal to 100 nm.

6. The airfoil structure suitable for anti-icing and de-icing according to claim 3, 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.

7. The airfoil structure suitable for anti-icing and de-icing according to any one of claims 1 to 6, characterized in that: The first temperature zone and the second temperature zone have the same temperature rise response speed.

8. The airfoil structure suitable for anti-icing and de-icing according to any one of claims 1 to 6, characterized in that: The first temperature zone and the second temperature zone have the same temperature drop response speed.

9. The airfoil structure suitable for anti-icing and de-icing according to claim 2 or 3, characterized in that: The fiber monofilament (3) is quartz fiber, glass fiber, ceramic fiber, carbon fiber, alumina fiber or boron fiber.

10. The airfoil structure suitable for anti-icing and de-icing according to claim 1, characterized in that: The shell (1) comprises a surface coating, a heat-conducting layer and an insulating layer arranged in sequence from the outer side of the shell toward the electric heating element (2), and an insulating layer, a heat-conducting layer and a surface coating arranged in sequence from the electric heating element (2) toward the inner side of the shell.

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