CN114104299A - Super-hydrophobic coating plasma and graphene electric heating composite ice preventing and removing device and method - Google Patents
Super-hydrophobic coating plasma and graphene electric heating composite ice preventing and removing device and method Download PDFInfo
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- CN114104299A CN114104299A CN202111427716.6A CN202111427716A CN114104299A CN 114104299 A CN114104299 A CN 114104299A CN 202111427716 A CN202111427716 A CN 202111427716A CN 114104299 A CN114104299 A CN 114104299A
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 101
- 229910021389 graphene Inorganic materials 0.000 title claims abstract description 101
- 230000003075 superhydrophobic effect Effects 0.000 title claims abstract description 54
- 239000011248 coating agent Substances 0.000 title claims abstract description 53
- 238000000576 coating method Methods 0.000 title claims abstract description 53
- 239000002131 composite material Substances 0.000 title claims abstract description 14
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000005485 electric heating Methods 0.000 title claims description 10
- 230000004888 barrier function Effects 0.000 claims abstract description 28
- 230000002265 prevention Effects 0.000 claims abstract description 18
- 239000000758 substrate Substances 0.000 claims description 13
- 239000007788 liquid Substances 0.000 claims description 8
- 230000002209 hydrophobic effect Effects 0.000 claims description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 6
- 239000004642 Polyimide Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- 229920001721 polyimide Polymers 0.000 claims description 4
- 230000009471 action Effects 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 claims description 3
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims description 2
- 230000001070 adhesive effect Effects 0.000 claims description 2
- 238000013329 compounding Methods 0.000 claims 2
- 238000005516 engineering process Methods 0.000 abstract description 6
- 230000004044 response Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000004134 energy conservation Methods 0.000 abstract description 2
- 238000005265 energy consumption Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 239000011889 copper foil Substances 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000011521 glass Substances 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
- 239000002103 nanocoating Substances 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
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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
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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
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- 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
A dielectric barrier discharge plasma exciter of a graphene electrothermal film base is provided: the surface of the graphene electrothermal film 1 is added with an insulating layer 2, the surface of the insulating layer 2 is plated with a bare electrode 3, 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 plasma and graphene electrothermal composite ice prevention and removal device based on the exciter and the super-hydrophobic coating plasma and graphene electrothermal composite ice prevention and removal method based on the device are also provided. Compared with the existing anti-icing technology, the anti-icing device has the advantages of quick response, simple structure, high efficiency, energy conservation, no ecological pollution, obvious anti-icing effect and easiness in realization, and can scientifically and reasonably encrypt the anti-icing device according to the icing severity degree, thereby having good engineering application prospect.
Description
Technical Field
The invention belongs to an anti-icing and deicing device and method for the surface of an aircraft, relates to a graphene electrothermal film, plasma excitation and a super-hydrophobic coating, and particularly relates to an anti-icing and deicing device and method combining super-hydrophobic coating plasma and the graphene electrothermal film.
Background
Aircraft icing is widely recognized as one of the major hazards of aviation flight. When the aircraft passes through a cloud layer under ice-accumulating meteorological conditions, supercooled water drops in the cloud layer impact the windward side of the aircraft, so that the surfaces of parts (wings, windshield glass, empennage, engine lips, airspeed tubes and the like) on the windward side of the aircraft are iced, particularly the icing near a stagnation point is more serious, and the icing of key parts of the aircraft can seriously influence the aerodynamic performance of the aircraft, thereby causing the rapid reduction of the safety performance of the aircraft. For example, icing at the leading edge of the wing and the tail wing can change the aerodynamic shape of the aircraft to different degrees, violate the design criteria of the aircraft, rapidly reduce the lift force, rapidly increase the drag force, and seriously affect the maneuverability and stability of the aircraft. Therefore, the ice preventing and removing device is required to be arranged on the easy-to-freeze part of the airplane, and the safety performance of the airplane is improved.
According to different ice prevention and removal energy input modes, the main ice prevention and removal modes at present comprise an electric heating ice prevention and removal system, a gas heating ice prevention system, a mechanical ice removal system, a superhydrophobic material ice prevention and removal system and the like. The first two anti-icing and deicing methods are applied, and an electric heating anti-icing and deicing system is high in reliability and easy to realize, but is slow in response and high in power consumption due to the fact that an insulating skin is heated; the pneumatic anti-icing technology is simple to maintain and reliable in work, but the performance of the engine is influenced by air bleed from the engine or the auxiliary engine, and the energy utilization rate is low. Based on the good physical and chemical characteristics of the nano coating, researchers coat the super-hydrophobic coating on the surface of the lead so as to solve the anti-icing problem of the high-voltage line and obtain a good anti-icing effect. Research shows that the super-hydrophobic coating can change the property of ice coating and reduce the adhesion between an ice layer and a substrate. At present, the plasma anti-icing technology is rapidly developed, but the problem of energy consumption is always a problem for restricting the application of the plasma anti-icing technology. The low energy consumption problem of airplane deicing is very important in all countries, 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. But the icing phenomenon on the surface of an airplane part cannot be avoided by only depending on the super-hydrophobic surface, and the energy consumption for removing all ice layers by using a plasma deicing method is too large. It is therefore desirable to find a solution.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a dielectric barrier discharge plasma exciter of a graphene electrothermal film substrate, which specifically comprises the following 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 from top to bottom by the graphene electrothermal film 1, the insulating layer 2 and the bare electrode 3, and coating a super-hydrophobic coating 4 on the whole lower surface of the three-layer structure; 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 area of the lower surface of the graphene electrothermal film 1 is larger than that of the lower surface of the exposed electrode 3; wherein
The insulating layer 2 is a rectangular sheet, and the size of the area thereof can be set according to the ice control demand. The two sides of the insulating layer 2 are respectively attached with the bare electrode 3 and the graphene electrothermal film 1;
the exposed electrodes 3 are distributed in a grid shape, the whole body is rectangular, and the intervals of the grids are reasonably arranged according to the ice preventing and removing area; the exposed electrodes 3 comprise a plurality of strip electrodes which are arranged in parallel along the length direction, the length of each strip electrode is selected according to the requirement, two ends of each electrode are fixedly connected together through two transverse electrodes which are arranged in parallel along the width direction, the width and the thickness of each transverse electrode are consistent with those of each strip electrode, and the length of each transverse electrode is the maximum arrangement length of each strip electrode along the width direction; the exposed electrode 3 is rectangular as a whole, and four sides of the exposed electrode are respectively parallel to the corresponding sides of the insulating layer 2 and keep a certain distance; 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 an anti-icing and deicing area;
after the three-layer structure is formed, a super-hydrophobic coating 4 is additionally coated on the lower surface of the three-layer structure to form the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate, and the projection of the super-hydrophobic coating 4 is superposed with the projection of the graphene electrothermal film 1; if viewed from the bottom to the top, part of the insulating layer 2 is exposed from the grid gaps of the exposed electrode 3, and the super-hydrophobic coating 4 is directly coated on the exposed part of the insulating layer 2.
In the specific embodiment of the invention, the central points of the graphene electrothermal film 1, the insulating layer 2, the exposed electrode 3 and the super-hydrophobic coating 4 are overlapped.
In one embodiment of the invention, the strip electrodes have a width of 1mm to 10 mm; the thickness is 0.06mm-0.2 mm; the length of the strip electrode can be selected according to requirements; the distance between the adjacent strip electrodes is 5 mm-10 mm.
In one embodiment of the present invention, the bare electrode 3 is made of metal or metal alloy material with relatively high conductivity coefficient, and the width of the long electrode is 2 mm; the thickness is 0.08 mm; the distance between adjacent strip electrodes is 10 mm.
In another embodiment of the invention, the thickness of the graphene electrothermal film 1 is 0.06-0.2 mm; four sides of the exposed electrode 3 are 1-5mm shorter than the graphene electrothermal film 1.
In another embodiment of the present invention, four sides of the exposed electrode 3 are shorter than the length of the graphene electrothermal film 1 by 3 mm.
In yet another embodiment of the invention, the superhydrophobic coating 4 is a SiC hydrophobic material; the high-temperature-resistant adhesive is coated on the upper surface of the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate, so that the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate can be repeatedly and circularly adhered to the surface needing ice prevention and removal according to the ice prevention and removal requirements; the insulating layer 2 is made of a multilayer polyimide tape or other high-temperature resistant composite materials with equivalent dielectric constants.
The super-hydrophobic coating plasma and graphene electrothermal composite ice preventing and removing device adopts the dielectric barrier discharge plasma exciter with the graphene electrothermal film substrate, and specifically provides the super-hydrophobic coating plasma and graphene electrothermal composite ice preventing and removing device
The exposed electrode 3 is a high-voltage electrode of a dielectric barrier discharge plasma exciter on the basis of a graphene electrothermal film; the bare electrode 3 is connected with the high-voltage end of the airborne pulse plasma power supply 6 through a lead, and the graphene electrothermal film 1 is connected with the low-voltage end of the airborne pulse plasma power supply 6 through a lead; the positive pole and the negative pole 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 greater than 10mm, and the connecting line of the two contacts is parallel to one edge of the graphene electrothermal film 1 and keeps a certain distance with the edge, wherein the distance is in a range of 5-20 mm.
In addition, a super-hydrophobic coating plasma and graphene electric heating composite anti-icing and deicing method is further provided, and the super-hydrophobic coating plasma and graphene electric heating composite anti-icing and deicing device is specifically as follows:
when super-cooled water drops impact the wing, due to the existence of the super-hydrophobic coating 4, under the action of a hydrophobic effect, the contact angle between the liquid drops and the surface is more than 150 degrees, and part of the liquid drops can directly slide off the surface of the wing; at the moment, the airborne pulse plasma power supply 6 and the low-voltage direct-current power supply 5 are turned on, a plasma area is formed at the gap between the adjacent electrode strips of the exposed electrode 3, and the plasma has the function of instantly heating air and the wall surface; in addition, the graphene electrothermal film 1 can uniformly heat the surface of the wing; the double functions ensure that the supercooled water drops can not be frozen on the surface of the wing, and the aim of ice prevention is achieved.
The invention relates to an anti-icing and deicing device and method combining super-hydrophobic coating plasma and a graphene electrothermal film. The whole super-hydrophobic coating plasma and graphene electric heating film compounded ice prevention and removal device is installed in a groove of an aircraft surface skin, the surface smoothness of the aircraft is guaranteed, the pneumatic appearance of the aircraft is not affected, and the ice prevention and removal device can be flexibly arranged according to the icing difficult and easy area on the surface of the aircraft. Aiming at the problems that the icing is easy to happen near the stagnation point of the windward side of the aircraft, and the icing conditions of other areas are weak, the exposed electrode area in the deicing device is reasonably arranged, the exposed electrode is arranged at the position where the icing is easy to happen most, the response speed is guaranteed, and the energy utilization is scientific and reasonable.
Compared with the existing anti-icing technology, the anti-icing technology applying the super-hydrophobic coating plasma and the graphene electrothermal film composite has the advantages of quick response, simple structure, high efficiency, energy conservation, no ecological pollution, scientific and reasonable encryption and anti-icing device according to the icing severity, obvious anti-icing effect, easy realization and good engineering application prospect.
Drawings
The novel gradient distributed plasma deicing device and the novel gradient distributed plasma deicing method are further described in the following with reference to the drawings and the embodiment.
Fig. 1 is a schematic diagram of an anti-icing device compounded by a super-hydrophobic coating plasma and a graphene electrothermal film, wherein fig. 1(a), (b) and (c) respectively show a front view, a top view and a perspective view of the anti-icing device compounded by the super-hydrophobic coating plasma and the graphene electrothermal film;
FIG. 2 shows a schematic diagram of the connection circuitry of the present invention;
in the figure: 1. graphene electrothermal film 2, insulating layer 3, exposed electrode 4, super-hydrophobic coating 5, low-voltage direct-current power supply 6 and airborne pulse plasma power supply
Detailed Description
The technical scheme adopted by the invention 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 a bare electrode 3, 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. In fig. 1(a), in order to visually display the arrangement of the exposed electrode 3, only a part of the super-hydrophobic coating 4 is shown in the figure, in practice, 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 area of the lower surface of the graphene electrothermal film 1 is larger than that of the lower surface of the exposed electrode 3.
In one embodiment of the present invention, the insulating layer 2 is formed by adhering multiple layers of polyimide tapes or other high temperature resistant composite materials with comparable dielectric constants. In one embodiment of the present invention, the insulating layer 2 is formed by bonding 3 or more layers of polyimide tape.
The exposed electrodes 3 are distributed in a grid shape, are rectangular as a whole, and can reasonably arrange the intervals of the grids according to the anti-icing and anti-icing area. The exposed electrode 3 includes a plurality of strip electrodes arranged in parallel with each other along the length direction (the length direction is the longitudinal direction of fig. 1 (b)), and both ends of the electrodes are fixedly connected together by two transverse electrodes arranged in parallel with each other along the width direction (the width direction is the transverse direction of fig. 1 (b)); the exposed electrode 3 is rectangular, and four sides of the exposed electrode are parallel to the corresponding sides of the insulating layer 2 respectively and keep a certain distance. In one embodiment of the invention, the bare electrode 3 material is copper foil (metal or metal alloy material with relatively high conductivity coefficient), and the width of the long electrode is 1mm-10mm, preferably 2 mm; the thickness is 0.06mm-0.2mm, preferably 0.08 mm; the length of the strip electrodes can be selected according to requirements. The distance between adjacent strip electrodes is 5mm to 10mm, preferably 10 mm. The width and the thickness of the transverse electrodes are consistent with those of the strip electrodes, and the length of the transverse electrodes is the maximum arrangement length of the strip electrodes along the width direction. The bare electrode 3 is attached to one surface of the insulating layer 2, and the projection of the bare 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 cannot 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 an anti-icing area, and in one embodiment of the invention, the thickness of the graphene electrothermal film 1 is 0.06-0.2 mm. Four sides of the exposed electrode 3 are shorter than the graphene electrothermal film 1 by 1-5mm, preferably 3 mm. And the projection of the periphery is positioned at the projection center of the graphene electrothermal film 1.
After the three-layer structure is formed, the super-hydrophobic coating 4 is additionally coated on the lower surface of the three-layer structure to form the dielectric barrier discharge plasma exciter of the graphene electrothermal film base, and the projection of the super-hydrophobic coating 4 is superposed with the projection of the graphene electrothermal film 1. If viewed from the bottom to the top, part of the insulating layer 2 is exposed from the grid gaps of the exposed electrode 3, and the super-hydrophobic coating 4 is directly coated on the exposed part of the insulating layer 2. In one embodiment of the present invention, the super-hydrophobic coating 4 is a hydrophobic SiC material, which has both hydrophobic function and can stabilize the electric field during the discharge process.
The dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate is a flexible film. Also, in one embodiment of the invention, application to the wing surface is facilitated. The upper surface (namely the outer surface of the graphene electrothermal film 1 back to the insulating layer 2) of the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate is coated with high-temperature-resistant 3M glue, so that the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate can be repeatedly and circularly adhered to the surface needing ice prevention and removal according to the ice prevention and removal requirements.
The invention also provides a super-hydrophobic coating plasma and graphene electrothermal composite anti-icing and deicing device, which utilizes a dielectric barrier discharge plasma exciter of a graphene electrothermal film substrate. Specifically, the bare 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 lead, and the graphene electrothermal film 1 is connected with the low-voltage end of the airborne pulse plasma power supply 6 through a lead. 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 one edge (any one of the upper edge, the lower edge, the left edge and the right edge) of the graphene electrothermal film 1, and a certain distance is kept between the connecting line and the edge, wherein the distance ranges from 5mm to 20mm, and is preferably 10 mm. When super-cooled water drops impact wings, due to the existence of the super-hydrophobic coating 4, under the action of a hydrophobic effect, the contact angle between the liquid drops and the surfaces 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 static on the surfaces, the liquid drops can keep a better spherical shape on the super-hydrophobic surfaces, 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 a hydrophobic surface from 90 degrees to 150 degrees, and the contact angle smaller than 90 degrees is a hydrophilic surface. At the moment, the airborne pulse plasma power supply 6 and the low-voltage direct-current power supply 5 are turned on, a plasma area is formed in the gap between the adjacent electrode strips of the exposed electrode 3, and the plasma has the function of instantly heating air and the wall surface. In addition, the graphene electrothermal film 1 can uniformly heat the surface of the wing. The double functions ensure that the supercooled water drops can not be frozen on the surface of the wing, and the aim of ice prevention is achieved.
Claims (10)
1. The dielectric barrier discharge plasma exciter based on the graphene electrothermal film is characterized in that a layer of 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 a super-hydrophobic coating 4 is coated on the whole lower surface of the three-layer structure; 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 area of the lower surface of the graphene electrothermal film 1 is larger than that of the lower surface of the exposed electrode 3; wherein
The insulating layer 2 is a rectangular sheet, and the size of the area thereof can be set according to the ice control demand. The two sides of the insulating layer 2 are respectively attached with the bare electrode 3 and the graphene electrothermal film 1;
the exposed electrodes 3 are distributed in a grid shape, the whole body is rectangular, and the intervals of the grids are reasonably arranged according to the ice preventing and removing area; the exposed electrodes 3 comprise a plurality of strip electrodes which are arranged in parallel along the length direction, the length of each strip electrode is selected according to the requirement, two ends of each electrode are fixedly connected together through two transverse electrodes which are arranged in parallel along the width direction, the width and the thickness of each transverse electrode are consistent with those of each strip electrode, and the length of each transverse electrode is the maximum arrangement length of each strip electrode along the width direction; the exposed electrode 3 is rectangular as a whole, and four sides of the exposed electrode are respectively parallel to the corresponding sides of the insulating layer 2 and keep a certain distance; 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 an anti-icing and deicing area;
after the three-layer structure is formed, a super-hydrophobic coating 4 is additionally coated on the lower surface of the three-layer structure to form the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate, and the projection of the super-hydrophobic coating 4 is superposed with the projection of the graphene electrothermal film 1; if viewed from the bottom to the top, part of the insulating layer 2 is exposed from the grid gaps of the exposed electrode 3, and the super-hydrophobic coating 4 is directly coated on the exposed part of the insulating layer 2.
2. The graphene electrothermal film based dielectric barrier discharge plasma exciter according to claim 1, wherein the central points of the graphene electrothermal film 1, the insulating layer 2, the exposed electrode 3 and the super-hydrophobic coating 4 coincide.
3. The graphene electrocaloric film based dielectric barrier discharge plasma exciter of claim 1, wherein the strip electrode width is 1mm to 10 mm; the thickness is 0.06mm-0.2 mm; the length of the strip electrode can be selected according to requirements; the distance between the adjacent strip electrodes is 5 mm-10 mm.
4. The graphene electrocaloric film based dielectric barrier discharge plasma exciter of claim 3, wherein the exposed electrode 3 material is a metal or metal alloy material with a relatively high electrical conductivity, and the width of the elongated electrode is 2 mm; the thickness is 0.08 mm; the distance between adjacent strip electrodes is 10 mm.
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 0.06-0.2 mm; four sides of the exposed electrode 3 are 1-5mm shorter than the graphene electrothermal film 1.
6. The graphene electrothermal film based dielectric barrier discharge plasma exciter of claim 5, wherein the exposed electrodes 3 have four sides shorter by 3mm than the graphene electrothermal film 1.
7. The graphene electrocaloric film based dielectric barrier discharge plasma exciter of claim 1, wherein the superhydrophobic coating 4 is a SiC hydrophobic material; the high-temperature-resistant adhesive is coated on the upper surface of the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate, so that the dielectric barrier discharge plasma exciter of the graphene electrothermal film substrate can be repeatedly and circularly adhered to the surface needing ice prevention and removal according to the ice prevention and removal requirements; the insulating layer 2 is made of a multilayer polyimide tape or other high-temperature resistant composite materials with equivalent dielectric constants.
8. The device for preventing and killing ice by combining super-hydrophobic coating plasma and graphene electrothermal is characterized by adopting the graphene electrothermal film-based dielectric barrier discharge plasma exciter according to any one of claims 1 to 8, in particular to a device for preventing and killing ice
The exposed electrode 3 is a high-voltage electrode of a dielectric barrier discharge plasma exciter on the basis of a graphene electrothermal film; the bare electrode 3 is connected with the high-voltage end of the airborne pulse plasma power supply 6 through a lead, and the graphene electrothermal film 1 is connected with the low-voltage end of the airborne pulse plasma power supply 6 through a lead; the positive pole and the negative pole of the low-voltage direct-current stabilized power supply 5 are respectively connected with two contacts on the graphene electrothermal film 1.
9. The superhydrophobic coating plasma and graphene electrothermal composite anti-icing and deicing device according to claim 8, wherein the distance between two contacts is greater than 10mm, a connecting line of the two contacts is parallel to one edge of the graphene electrothermal film 1 and keeps a certain distance with the edge, and the distance range is 5-20 mm.
10. The method for preventing and killing ice by electrically and compositely compounding the super-hydrophobic coating plasma and the graphene is characterized in that the device for preventing and killing ice by electrically and compositely compounding the super-hydrophobic coating plasma and the graphene as claimed in claim 8 or 9 is adopted, and the method specifically comprises the following steps:
when super-cooled water drops impact the wing, due to the existence of the super-hydrophobic coating 4, under the action of a hydrophobic effect, the contact angle between the liquid drops and the surface is more than 150 degrees, and part of the liquid drops can directly slide off the surface of the wing; at the moment, the airborne pulse plasma power supply 6 and the low-voltage direct-current power supply 5 are turned on, a plasma area is formed at the gap between the adjacent electrode strips of the exposed electrode 3, and the plasma has the function of instantly heating air and the wall surface; in addition, the graphene electrothermal film 1 can uniformly heat the surface of the wing; the double functions ensure that the supercooled water drops can not be frozen on the surface of the wing, and the aim of ice prevention is achieved.
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 true CN114104299A (en) | 2022-03-01 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6027075A (en) * | 1997-06-16 | 2000-02-22 | Trustees Of Dartmouth College | Systems and methods for modifying ice adhesion strength |
| US20070194179A1 (en) * | 2004-03-03 | 2007-08-23 | Giamati Michael J | Aircraft wing with electrothermal deicing and/or anti-icing device |
| US20140151353A1 (en) * | 2011-05-26 | 2014-06-05 | Eads Deutschland Gmbh | Composite Structure Having an Ice Protection Device, and Production Method |
| 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 |
-
2021
- 2021-11-26 CN CN202111427716.6A patent/CN114104299B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6027075A (en) * | 1997-06-16 | 2000-02-22 | Trustees Of Dartmouth College | Systems and methods for modifying ice adhesion strength |
| US20070194179A1 (en) * | 2004-03-03 | 2007-08-23 | Giamati Michael J | Aircraft wing with electrothermal deicing and/or anti-icing device |
| US20140151353A1 (en) * | 2011-05-26 | 2014-06-05 | Eads Deutschland Gmbh | Composite Structure Having an Ice Protection Device, and Production Method |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 郑海坤;常士楠;赵媛媛;: "超疏水/超润滑表面的防疏冰机理及其应用", 化学进展, no. 01, pages 102 - 118 * |
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