CN114104299B - Device and method for preventing and removing ice by compounding superhydrophobic coating plasma and graphene electric heating - Google Patents
Device and method for preventing and removing ice by compounding superhydrophobic coating plasma and graphene electric heating Download PDFInfo
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- CN114104299B CN114104299B CN202111427716.6A CN202111427716A CN114104299B CN 114104299 B CN114104299 B CN 114104299B CN 202111427716 A CN202111427716 A CN 202111427716A CN 114104299 B CN114104299 B CN 114104299B
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 98
- 229910021389 graphene Inorganic materials 0.000 title claims abstract description 98
- 239000011248 coating agent Substances 0.000 title claims abstract description 48
- 238000000576 coating method Methods 0.000 title claims abstract description 48
- 230000003075 superhydrophobic effect Effects 0.000 title claims abstract description 47
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000005485 electric heating Methods 0.000 title claims description 8
- 238000013329 compounding Methods 0.000 title description 4
- 230000004888 barrier function Effects 0.000 claims abstract description 29
- 239000002131 composite material Substances 0.000 claims abstract description 8
- 230000000694 effects Effects 0.000 claims abstract description 6
- 230000002209 hydrophobic effect Effects 0.000 claims description 8
- 230000002265 prevention Effects 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 7
- 239000004642 Polyimide Substances 0.000 claims description 5
- 229920001721 polyimide Polymers 0.000 claims description 5
- 238000010438 heat treatment Methods 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 4
- 230000009471 action Effects 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 abstract description 6
- 230000004044 response Effects 0.000 abstract description 4
- 239000007788 liquid Substances 0.000 description 6
- 238000005265 energy consumption Methods 0.000 description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 239000011889 copper foil Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000005660 hydrophilic surface Effects 0.000 description 1
- 230000005661 hydrophobic surface Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000002103 nanocoating Substances 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/10—Heater elements characterised by the composition or nature of the materials or by the arrangement of the conductor
- H05B3/12—Heater elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material
- H05B3/14—Heater elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
- H05B3/145—Carbon only, e.g. carbon black, graphite
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/2406—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes
Abstract
Providing a dielectric barrier discharge plasma exciter based on a graphene electrothermal film: an insulating layer 2 is added on the surface of the graphene electrothermal film 1, a bare electrode 3 is plated on the surface of the insulating layer 2, the graphene electrothermal film 1, the insulating layer 2 and the bare electrode 3 form a three-layer structure from top to bottom, and the whole lower surface of the three-layer structure is coated with a super-hydrophobic coating 4. The device and the method for preventing and removing ice by combining the superhydrophobic coating plasma and the graphene electrothermal composite are also provided. Compared with the existing anti-icing technology, the invention has the advantages of quick response, simple structure, high efficiency, energy saving, ecology and no pollution, can scientifically and reasonably encrypt the anti-icing device according to the icing severity, has obvious anti-icing effect, is easy to realize, and has good engineering application prospect.
Description
Technical Field
The invention belongs to a device and a method for preventing and removing ice on the surface of an aircraft, relates to a graphene electrothermal film, plasma excitation and a super-hydrophobic coating, and in particular relates to a device and a method for preventing and removing ice by compounding plasma of the super-hydrophobic coating and the graphene electrothermal film.
Background
Aircraft icing is widely recognized as one of the major hazards of aviation flight. When an aircraft passes through a cloud layer of ice accumulation meteorological conditions, supercooled water drops in the cloud layer collide with the windward side of the aircraft, so that the surfaces of windward parts (wings, windshields, tail wings, engine lips, airspeed tubes and the like) of the aircraft are frozen, especially, the vicinity of stagnation points are frozen more seriously, and the aerodynamic performance of the aircraft is seriously affected by the icing of key parts of the aircraft, so that the safety performance of the aircraft is rapidly reduced. For example, the front edges of wings and tail wings are frozen, so that the aerodynamic shape of the aircraft can be changed to different degrees, the design rule of the aircraft is violated, the lift force is rapidly reduced, the resistance is rapidly increased, and the maneuvering performance and the stability performance of the aircraft are seriously affected. Therefore, the ice preventing and removing device is required to be arranged at the ice prone position of the aircraft, so that the safety performance of the aircraft is improved.
According to different deicing energy input modes, the main deicing modes at present comprise an electrothermal deicing system, an air-thermal deicing system, a mechanical deicing system, a superhydrophobic material deicing system and the like. The first two ice control methods are applied, and the electric heating ice control system has high reliability and is easy to realize, but the response is slow and the power consumption is higher due to the heating of the insulating skin; pneumatic anti-icing technology is simple to maintain and reliable in operation, but bleed air from an engine or an auxiliary engine can affect engine performance, and energy utilization rate is low. Based on good physicochemical properties of the nano coating, researchers coat the super-hydrophobic coating on the surface of the wire, so as to solve the anti-icing problem of the high-voltage line and obtain a good anti-icing effect. The research shows that the super-hydrophobic coating can change the property of ice coating and reduce the adhesion between the ice layer and the matrix. At present, a plasma deicing technology rapidly develops, but the problem of energy consumption is always a problem which restricts the application of the plasma deicing technology. All countries are very important to see the problem of low energy consumption of aircraft deicing, and the super-hydrophobic coating and the surface coating prepared by the super-hydrophobic coating can reduce the generation of icing and reduce the energy consumption required by deicing. However, the icing phenomenon on the surface of the aircraft component cannot be completely eradicated by simply relying on the superhydrophobic surface, and the energy consumption for removing all the ice layers by using the plasma ice removing method is too large. There is a need to find a solution.
Disclosure of Invention
Aiming at the problems existing in the prior art, the invention provides a dielectric barrier discharge plasma exciter based on a graphene electrothermal film, which comprises the following specific steps: adding an insulating layer 2 on the surface of a graphene electrothermal film 1, plating a bare electrode 3 on the surface of the insulating layer 2, forming a three-layer structure of the graphene electrothermal film 1, the insulating layer 2 and the bare electrode 3 from top to bottom, and coating the whole lower surface of the three-layer structure with a super-hydrophobic coating 4; the super-hydrophobic coating 4 completely covers the projection part of the graphene electrothermal film 1 on the lower surface of the three-layer structure, and the lower surface area of the graphene electrothermal film 1 is larger than the lower surface area of the exposed electrode 3; wherein the method comprises the steps of
The insulating layer 2 is a rectangular sheet, and the area size thereof can be set according to the ice control demand. The exposed electrode 3 and the graphene electrothermal film 1 are respectively attached to two sides of the insulating layer 2;
the exposed electrodes 3 are distributed in a grid shape, are rectangular as a whole, and are reasonably distributed according to the intervals of grids in the anti-icing area; the exposed electrode 3 comprises a plurality of strip electrodes which are arranged in parallel along the length direction, the lengths of the strip electrodes are selected according to requirements, two ends of the strip electrodes are fixedly connected together through two transverse electrodes which are arranged in parallel along the width direction, the width and the thickness of the transverse electrodes are consistent with those of the strip electrodes, and the length is the maximum arrangement length of the strip electrodes along the width direction; the four sides of the overall rectangular exposed electrode 3 are respectively parallel to the corresponding sides of the insulating layer 2, and a certain interval is kept between the four sides; the exposed electrode 3 is attached to one surface of the insulating layer 2, and the projection of the exposed electrode 3 on the horizontal plane does not exceed the projection edge of the insulating layer 2 on the horizontal plane;
the graphene electrothermal film 1 is used as an electric heating module and also used as a low-voltage electrode of a dielectric barrier discharge plasma exciter, the graphene electrothermal film 1 is attached to the other surface of the insulating layer 2, and the projection of the graphene electrothermal film 1 on the horizontal plane does not exceed the projection edge of the insulating layer 2 on the horizontal plane; the size of the graphene electrothermal film 1 can be determined according to the size of the deicing prevention area;
after the three-layer structure is formed, a super-hydrophobic coating 4 is coated on the lower surface of the three-layer structure, so that the dielectric barrier discharge plasma exciter based on the graphene electrothermal film is formed, and the projection of the super-hydrophobic coating 4 coincides with the projection of the graphene electrothermal film 1; if viewed from the bottom to the top, a portion of the insulating layer 2 is exposed from the grid gaps of the bare electrode 3, and the superhydrophobic coating 4 is also directly coated on the exposed portion of the insulating layer 2.
In the specific embodiment of the invention, the center points of the graphene electrothermal film 1, the insulating layer 2, the exposed electrode 3 and the superhydrophobic coating 4 are coincident.
In one embodiment of the invention, the elongate electrodes have a width of 1mm to 10mm; the thickness is 0.06mm-0.2mm; the length of the strip electrode can be selected according to the requirement; the spacing between adjacent strip electrodes is 5 mm-10 mm.
In one embodiment of the invention, the exposed electrode 3 material is a metal or metal alloy material with relatively high conductivity, and the width of the strip electrode is 2mm; the thickness is 0.08mm; the spacing between adjacent strip electrodes is 10mm.
In another embodiment of the invention, the thickness of the graphene electrothermal film 1 is 0.06-0.2mm; the length of the four sides of the exposed electrode 3 is 1-5mm shorter than that of the graphene electrothermal film 1.
In another embodiment of the invention, the four sides of the exposed electrode 3 are 3mm shorter than the graphene electrothermal film 1.
In yet another embodiment of the invention, the superhydrophobic coating 4 is a SiC hydrophobic material; the upper surface of the dielectric barrier discharge plasma exciter based on the graphene electrothermal film is coated with a high-temperature resistant adhesive, so that the dielectric barrier discharge plasma exciter based on the graphene electrothermal film can be circularly stuck for many times on the surface needing ice prevention and removal according to the ice prevention and removal requirement; the insulating layer 2 is a multi-layer polyimide tape bonded or other high temperature resistant composite material with equivalent dielectric constant.
The dielectric barrier discharge plasma exciter based on the graphene electrothermal film is adopted, and the dielectric barrier discharge plasma exciter is specifically
The exposed electrode 3 is a high-voltage electrode of the dielectric barrier discharge plasma exciter based on the graphene electrothermal film; the exposed electrode 3 is connected with the high-voltage end of the airborne pulse plasma power supply 6 through a wire, and the graphene electrothermal film 1 is connected with the low-voltage end of the airborne pulse plasma power supply 6 through a wire; the positive electrode and the negative electrode of the low-voltage direct-current stabilized power supply 5 are respectively connected with two contacts on the graphene electrothermal film 1.
In one embodiment of the invention, the distance between the two contacts is larger than 10mm, the connecting line of the two contacts is parallel to one side of the graphene electrothermal film 1, and a certain distance is kept between the connecting line and the edge, and the distance is in the range of 5-20mm.
In addition, the invention also provides a method for preventing and removing ice by adopting the electric heating composite ice removing device for the super-hydrophobic coating plasma and the graphene, which comprises the following steps:
when supercooled water drops strike the wing, due to the existence of the super-hydrophobic coating 4, the contact angle between the drops and the surface is larger than 150 degrees under the action of the hydrophobic effect, and part of the drops can directly slide off the surface of the wing; at the moment, an airborne pulse plasma power supply 6 and a low-voltage direct current power supply 5 are turned on, a plasma region is formed at the gap between the adjacent electrode strips of the exposed electrode 3, and the plasma has the effect of instantaneously heating air and a wall surface; in addition, the graphene electrothermal film 1 can uniformly heat the surface of the wing; the double functions ensure that supercooled water drops can not freeze on the surface of the wing, and the aim of anti-icing is achieved.
According to the device and method for preventing and removing ice by compounding the superhydrophobic coating plasma and the graphene electrothermal film, copper foil (metal or metal alloy with relatively high conductivity) is adopted as a bare electrode, the graphene electrothermal film is an embedded electrode, a plurality of layers of polyimide or high-temperature resistant composite materials with equivalent dielectric constants are adopted as insulating layers, the bare electrode is connected with a high-voltage end of an airborne pulse plasma power supply through a wire, and the graphene electrothermal film is simultaneously connected with a low-voltage end of the airborne pulse plasma power supply and an airborne direct current output end through the wire. The whole ultra-hydrophobic coating plasma and graphene electrothermal film combined deicing device is arranged in a groove of the aircraft surface skin, so that the aircraft surface is smooth, the aerodynamic appearance of the aircraft is not affected, and the deicing device can be flexibly arranged according to the icing difficulty area of the aircraft surface. Aiming at the situation that the aircraft is easy to freeze near the windward surface resident point, the icing condition of other areas is weak, the areas of exposed electrodes in the deicing device are reasonably distributed, the exposed electrodes are arranged at the most easily icing position, the quick response is ensured, and the energy utilization is scientific and reasonable.
Compared with the existing anti-icing technology which combines the super-hydrophobic coating plasma and the graphene electrothermal film, the anti-icing technology has the advantages of quick response, simple structure, high efficiency, energy conservation, ecology and no pollution, can scientifically and reasonably encrypt the anti-icing device according to the icing severity, has obvious anti-icing effect, is easy to realize, and has good engineering application prospect.
Drawings
The novel gradient-type plasma deicing device and method are further described below with reference to the accompanying drawings and embodiments.
Fig. 1 shows a schematic diagram of an ice control device composited by superhydrophobic coating plasma and a graphene electrothermal film, wherein fig. 1 (a), (b) and (c) show a front view, a top view and a perspective view of the ice control device composited by superhydrophobic coating plasma and a graphene electrothermal film respectively;
FIG. 2 shows a schematic diagram of the connection circuit of the present invention;
in the figure: 1. graphene electrothermal film 2, insulating layer 3, exposed electrode 4, superhydrophobic coating 5, low-voltage direct current power supply 6, and airborne pulse plasma power supply
Detailed Description
The technical scheme adopted for solving the technical problems is as follows: adding an insulating layer 2 on the surface of the graphene electrothermal film 1, wherein the insulating layer 2 is a rectangular sheet; the surface of the insulating layer 2 is plated with the exposed electrode 3, the graphene electrothermal film 1, the insulating layer 2 and the exposed electrode 3 form a three-layer structure from top to bottom, and the whole lower surface of the three-layer structure is coated with the super-hydrophobic coating 4. In fig. 1 (a), in order to intuitively show the arrangement manner of the exposed electrode 3, only a part of the superhydrophobic coating 4 is drawn in the figure, and in practice, the superhydrophobic coating 4 completely covers the projected portion of the graphene electrothermal film 1 on the lower surface of the three-layer structure, and the lower surface area of the graphene electrothermal film 1 is larger than the lower surface area of the exposed electrode 3.
In one embodiment of the present invention, the insulating layer 2 is formed by pasting a plurality of polyimide tapes, or other high temperature resistant composite materials with equivalent dielectric constants. In one embodiment of the present invention, the insulating layer 2 is formed by bonding 3 or more polyimide tapes.
The exposed electrodes 3 are distributed in a grid shape, and are rectangular overall, so that the spacing of the grids can be reasonably distributed according to the ice preventing and removing area. The bare electrode 3 includes a plurality of elongated electrodes arranged in parallel to each other in the longitudinal direction (the longitudinal direction is the longitudinal direction of fig. 1 (b)), and both ends of these electrodes are fixedly connected together by two lateral electrodes arranged in parallel to each other in the width direction (the lateral direction is the lateral direction of fig. 1 (b)); the four sides of the overall rectangular exposed electrode 3 are respectively parallel to the corresponding sides of the insulating layer 2, and a certain interval is kept between the four sides. In one embodiment of the invention, the bare electrode 3 material is copper foil (a metal or metal alloy material with relatively high conductivity), and the strip electrode has a width of 1mm-10mm, preferably 2mm; a thickness of 0.06mm to 0.2mm, preferably 0.08mm; the length of the strip electrode can be selected according to the requirement. The spacing between adjacent strip electrodes is 5mm to 10mm, preferably 10mm. The width and thickness of the transverse electrode are consistent with those of the strip electrodes, and the length is the maximum arrangement length of the strip electrodes along the width direction. The exposed electrode 3 is attached to one surface of the insulating layer 2, and the projection of the exposed electrode 3 on the horizontal plane does not exceed the projection edge of the insulating layer 2 on the horizontal plane.
The graphene electrothermal film 1 is used as an electric heating module and also used as a low-voltage electrode of a dielectric barrier discharge plasma exciter, the graphene electrothermal film 1 is attached to the other surface of the insulating layer 2, and the projection of the graphene electrothermal film 1 on the horizontal plane does not exceed the projection edge of the insulating layer 2 on the horizontal plane. The size of the graphene electrothermal film 1 can be determined according to the size of the deicing area, and in one embodiment of the invention, the thickness of the graphene electrothermal film 1 is 0.06-0.2mm. The length of the four sides of the exposed electrode 3 is 1-5mm shorter than that of the graphene electrothermal film 1, and is preferably 3mm. And the projection of the periphery is positioned at the central position of the projection of the graphene electrothermal film 1.
After the three-layer structure is formed, a Tu Chao hydrophobic coating 4 is added on the lower surface of the three-layer structure, so that the graphene electrothermal film-based dielectric barrier discharge plasma exciter is formed, and the projection of the superhydrophobic coating 4 coincides with the projection of the graphene electrothermal film 1. If viewed from the bottom to the top, a portion of the insulating layer 2 is exposed from the grid gaps of the bare electrode 3, and the superhydrophobic coating 4 is also directly coated on the exposed portion of the insulating layer 2. In one embodiment of the invention, the superhydrophobic coating 4 is a SiC hydrophobic material that has both a hydrophobic function and also stabilizes the electric field during discharge.
The graphene electrothermal film-based dielectric barrier discharge plasma exciter is a flexible film. And, in one embodiment of the invention, is conveniently applied to the wing surface. The upper surface of the dielectric barrier discharge plasma exciter based on the graphene electrothermal film (namely, the outer surface of the graphene electrothermal film 1 facing away from the insulating layer 2) is coated with high-temperature-resistant 3M glue, so that the dielectric barrier discharge plasma exciter based on the graphene electrothermal film can be circularly stuck for many times on the surface needing ice prevention and removal according to the ice prevention and removal requirement.
The invention also provides a device for preventing and removing ice by combining the super-hydrophobic coating plasma and the graphene electrothermal film, which utilizes the dielectric barrier discharge plasma exciter of the graphene electrothermal film base. Specifically, the exposed electrode 3 is a high-voltage electrode of a dielectric barrier discharge plasma exciter based on a graphene electrothermal film. The exposed electrode 3 is connected with the high-voltage end of the airborne pulse plasma power supply 6 through a wire, and the graphene electrothermal film 1 is connected with the low-voltage end of the airborne pulse plasma power supply 6 through a wire. The positive electrode and the negative electrode of the low-voltage direct-current stabilized power supply 5 are respectively connected with two contacts on the graphene electrothermal film 1, the distance between the two contacts is generally larger than 10mm, in one embodiment of the invention, the connecting line of the two contacts is parallel to a certain side (any side from top to bottom and left to right) of the graphene electrothermal film 1, and a certain distance is kept between the connecting line and the edge, and the distance is 5-20mm, preferably 10mm. When supercooled water drops strike the wing, due to the existence of the super-hydrophobic coating 4, under the action of the hydrophobic effect, the contact angle of the liquid drops and the surface is larger than 150 degrees (the contact angle of the liquid drops refers to the included angle between the tangent line at the contact point and the horizontal plane in the opposite direction when the liquid drops are at the surface, the liquid drops can keep a good sphere shape on the super-hydrophobic surface, so that the contact angle is larger, the surface with the contact angle larger than 150 degrees can be defined as the super-hydrophobic surface, the contact angle is 90-150 degrees as the hydrophobic surface, and the contact angle is smaller as the hydrophilic surface is smaller than 90 degrees, the contact area between the liquid drops and the surface is smaller, and the adhesion force is smaller), and part of the liquid drops can directly slide from the surface of the wing. At this time, the on-board pulse plasma power supply 6 and the low-voltage direct current power supply 5 are turned on, a plasma region is formed at the gap between the adjacent electrode strips of the exposed electrode 3, and the plasma has the effect of instantaneously heating air and the wall surface. In addition, the graphene electrothermal film 1 can uniformly heat the wing surface. The double functions ensure that supercooled water drops can not freeze on the surface of the wing, and the aim of anti-icing is achieved.
Claims (10)
1. The dielectric barrier discharge plasma exciter based on the graphene electrothermal film is characterized in that an insulating layer (2) is added on the surface of the graphene electrothermal film (1), a bare electrode (3) is plated on the surface of the insulating layer (2), the graphene electrothermal film (1), the insulating layer (2) and the bare electrode (3) form a three-layer structure from top to bottom, and the whole lower surface of the three-layer structure is coated with a super-hydrophobic coating (4); the super-hydrophobic coating (4) completely covers the projection part of the graphene electrothermal film (1) on the lower surface of the three-layer structure, and the lower surface area of the graphene electrothermal film (1) is larger than the lower surface area of the exposed electrode (3); wherein the method comprises the steps of
The insulating layer (2) is a rectangular sheet, the area of the insulating layer can be set according to the ice prevention and removal requirement, and the exposed electrode (3) and the graphene electrothermal film (1) are respectively attached to the two sides of the insulating layer (2);
the exposed electrodes (3) are distributed in a grid shape, are rectangular as a whole, and are reasonably distributed at intervals according to the anti-icing area; the exposed electrode (3) comprises a plurality of strip electrodes which are arranged in parallel along the length direction, the lengths of the strip electrodes are selected according to requirements, two ends of the electrodes are fixedly connected together through two transverse electrodes which are arranged in parallel along the width direction, the width and the thickness of the transverse electrodes are consistent with those of the strip electrodes, and the length is the maximum arrangement length of the strip electrodes along the width direction; the whole rectangular exposed electrode (3) has four sides respectively parallel to the corresponding sides of the insulating layer (2) and keeps a certain interval; the exposed electrode (3) is attached to one surface of the insulating layer (2), and the projection of the exposed electrode (3) on the horizontal plane does not exceed the projection edge of the insulating layer (2) on the horizontal plane;
the graphene electrothermal film (1) is used as an electric heating module and a low-voltage electrode of a dielectric barrier discharge plasma exciter, the graphene electrothermal film (1) is attached to the other surface of the insulating layer (2), and the projection of the graphene electrothermal film (1) on a horizontal plane does not exceed the projection edge of the insulating layer (2) on the horizontal plane; the size of the graphene electrothermal film (1) can be determined according to the size of the deicing area;
after the three-layer structure is formed, a super-hydrophobic coating (4) is coated on the lower surface of the three-layer structure, and the dielectric barrier discharge plasma exciter based on the graphene electrothermal film is formed, wherein the projection of the super-hydrophobic coating (4) is overlapped with the projection of the graphene electrothermal film (1); if the insulating layer (2) is seen from bottom to top, part of the insulating layer (2) is exposed from the grid gaps of the exposed electrode (3), and the superhydrophobic coating (4) is directly coated on the part of the exposed insulating layer (2).
2. The graphene electrothermal film-based dielectric barrier discharge plasma exciter according to claim 1, wherein the center points of the graphene electrothermal film (1), the insulating layer (2), the bare electrode (3) and the superhydrophobic coating (4) are coincident.
3. The graphene electrothermal film based dielectric barrier discharge plasma exciter of claim 1, wherein the elongate electrode width is 1mm-10mm; the thickness is 0.06mm-0.2mm; the length of the strip electrode can be selected according to the requirement; the spacing between adjacent strip electrodes is 5 mm-10 mm.
4. A graphene electrothermal film based dielectric barrier discharge plasma exciter according to claim 3, wherein the exposed electrode (3) material is a metal or metal alloy material with relatively high conductivity, and the width of the strip electrode is 2mm; the thickness is 0.08mm; the spacing between adjacent strip electrodes is 10mm.
5. The graphene electrothermal film-based dielectric barrier discharge plasma exciter according to claim 1, wherein the thickness of the graphene electrothermal film (1) is 0.06-0.2mm; the length of the four sides of the exposed electrode (3) is 1-5mm shorter than that of the graphene electrothermal film (1).
6. The dielectric barrier discharge plasma exciter based on the graphene electrothermal film according to claim 5, wherein the four sides of the exposed electrode (3) are 3mm shorter than the graphene electrothermal film (1).
7. The graphene electrothermal film-based dielectric barrier discharge plasma exciter according to claim 1, wherein the superhydrophobic coating (4) is a SiC hydrophobic material; the upper surface of the dielectric barrier discharge plasma exciter based on the graphene electrothermal film is coated with a high-temperature resistant adhesive, so that the dielectric barrier discharge plasma exciter based on the graphene electrothermal film can be circularly stuck for many times on the surface needing ice prevention and removal according to the ice prevention and removal requirement; the insulating layer (2) is a multi-layer polyimide tape adhesive or other high-temperature resistant composite materials with equivalent dielectric constants.
8. An ice control device by combining superhydrophobic coating plasma and graphene electrothermal film, which is characterized in that the device adopts the dielectric barrier discharge plasma exciter based on the graphene electrothermal film as claimed in any one of claims 1 to 7, in particular
The exposed electrode (3) is a high-voltage electrode of a dielectric barrier discharge plasma exciter based on a graphene electrothermal film; the exposed electrode (3) is connected with the high-voltage end of the airborne pulse plasma power supply (6) through a wire, and the graphene electrothermal film (1) is connected with the low-voltage end of the airborne pulse plasma power supply (6) through a wire; the positive electrode and the negative electrode of the low-voltage direct-current stabilized power supply (5) are respectively connected with two contacts on the graphene electrothermal film (1).
9. The device for preventing and removing ice by combining the super-hydrophobic coating plasma and the graphene electrothermal composite according to claim 8, wherein the distance between two contacts is larger than 10mm, the connecting line of the two contacts is parallel to one side of the graphene electrothermal film (1), and a certain distance is kept between the connecting line and the edge, and the distance is 5-20mm.
10. The method for preventing and removing ice by using the electric heating composite of the super-hydrophobic coating plasma and the graphene is characterized by comprising the following steps of:
when supercooled water drops impact the wing, due to the existence of the super-hydrophobic coating (4), the contact angle between the drops and the surface is larger than 150 degrees under the action of the hydrophobic effect, and part of the drops can directly slide off the surface of the wing; at the moment, an airborne pulse plasma power supply (6) and a low-voltage direct-current stabilized power supply (5) are turned on, a plasma region is formed at the gap between adjacent electrode strips of the exposed electrode (3), and the plasma has the effect of instantaneously heating air and a wall surface; in addition, the graphene electrothermal film (1) can uniformly heat the surface of the wing; the double functions ensure that supercooled water drops can not freeze on the surface of the wing, thereby achieving the anti-icing purpose.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111427716.6A CN114104299B (en) | 2021-11-26 | 2021-11-26 | Device and method for preventing and removing ice by compounding superhydrophobic coating plasma and graphene electric heating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111427716.6A CN114104299B (en) | 2021-11-26 | 2021-11-26 | Device and method for preventing and removing ice by compounding superhydrophobic coating plasma and graphene electric heating |
Publications (2)
| Publication Number | Publication Date |
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| CN114104299A CN114104299A (en) | 2022-03-01 |
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| US6027075A (en) * | 1997-06-16 | 2000-02-22 | Trustees Of Dartmouth College | Systems and methods for modifying ice adhesion strength |
| CN108545197A (en) * | 2018-05-03 | 2018-09-18 | 中国人民解放军空军工程大学 | The device and method for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma |
| CN109334998A (en) * | 2018-11-24 | 2019-02-15 | 中国人民解放军空军工程大学 | A kind of gradient distribution formula plasma de-icing device and method |
| WO2019078729A2 (en) * | 2017-10-20 | 2019-04-25 | Bergen Teknologioverforing As | Method for producing an icing protected arrangement and icing protected arrangement |
| CN110423523A (en) * | 2019-09-05 | 2019-11-08 | 中国航空制造技术研究院 | A kind of super-hydrophobic deicing composite coating and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7278610B2 (en) * | 2004-03-03 | 2007-10-09 | Goodrich Corporation | Aircraft wing with electrothermal deicing and/or anti-icing device |
| DE102011119844A1 (en) * | 2011-05-26 | 2012-12-13 | Eads Deutschland Gmbh | Composite structure with ice protection device and manufacturing process |
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| US6027075A (en) * | 1997-06-16 | 2000-02-22 | Trustees Of Dartmouth College | Systems and methods for modifying ice adhesion strength |
| WO2019078729A2 (en) * | 2017-10-20 | 2019-04-25 | Bergen Teknologioverforing As | Method for producing an icing protected arrangement and icing protected arrangement |
| CN108545197A (en) * | 2018-05-03 | 2018-09-18 | 中国人民解放军空军工程大学 | The device and method for carrying out the anti-deicing of wing is encouraged using rf (discharge) plasma |
| CN109334998A (en) * | 2018-11-24 | 2019-02-15 | 中国人民解放军空军工程大学 | A kind of gradient distribution formula plasma de-icing device and method |
| CN110423523A (en) * | 2019-09-05 | 2019-11-08 | 中国航空制造技术研究院 | A kind of super-hydrophobic deicing composite coating and preparation method thereof |
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