CN110856290A - Graphene composite membrane for preventing and removing ice, composite material structural member and preparation method - Google Patents
Graphene composite membrane for preventing and removing ice, composite material structural member and preparation method Download PDFInfo
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Classifications
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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
- H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
- H05B3/34—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
- C08J5/18—Manufacture of films or sheets
-
- 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
- H05B3/02—Details
- H05B3/03—Electrodes
-
- 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—Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J2367/00—Characterised by the use of polyesters obtained by reactions forming a carboxylic ester link in the main chain; Derivatives of such polymers
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
- C08J2379/00—Characterised by the use of macromolecular compounds obtained by reactions forming in the main chain of the macromolecule a linkage containing nitrogen with or without oxygen, or carbon only, not provided for in groups C08J2361/00 - C08J2377/00
- C08J2379/04—Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors
- C08J2379/08—Polyimides; Polyester-imides; Polyamide-imides; Polyamide acids or similar polyimide precursors
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/28—Nitrogen-containing compounds
- C08K2003/282—Binary compounds of nitrogen with aluminium
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
- C08K3/38—Boron-containing compounds
- C08K2003/382—Boron-containing compounds and nitrogen
- C08K2003/385—Binary compounds of nitrogen with boron
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K3/00—Use of inorganic substances as compounding ingredients
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Abstract
The invention relates to the technical field of aviation deicing, and provides a graphene composite film for deicing, a composite material structural member and a preparation method. Wherein, prevent removing ice with graphite alkene complex film includes: insulating heat-conducting layer, graphite alkene electrical heating rete and insulating thermal-protective layer. Wherein: the graphene electric heating film layer is arranged between the insulating heat conduction layer and the insulating heat insulation layer; the insulating layer comprises heat-resistant rubber, polyimide, aramid fiber, polyester, polyethylene and polypropylene; graphite alkene electrical heating rete includes: graphene composite membranes and electrodes. Wherein: the graphene composite film is attached to the surface of the graphene electric heating film layer; the electrodes are arranged at two ends of the graphene electric heating film layer; the insulating heat conducting layer is heat-resistant resin filled with high heat conducting ceramic particles. The graphene composite film provided by the embodiment of the invention can be stably combined with a composite material matrix, so that the thermal damage of electric heating to the composite material is reduced, and the anti-icing and deicing functions are stably realized under the condition that the mechanical property of the composite material matrix and the design requirement of an airplane are not influenced.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a graphene composite film for preventing and removing ice, a composite material structural member and a preparation method.
Background
When an airplane flies under icing meteorological conditions, supercooled water drops (water drops with the temperature lower than 0 ℃ and existing in a liquid state) in cloud layers impact the surface, and icing phenomena can occur, wherein the icing phenomena are serious on the surfaces of transparent parts such as wings, horizontal tail wings, the front edge of a vertical tail wing, the lip of an engine air inlet, air inlet parts (guide blades, supports and the like), propeller blades, fairing caps, windshields, cabin covers and the like, and the surfaces of atmospheric data detection devices such as airspeed tubes, attack angles, temperature sensors and the like. The ice accumulation on the surface of the airplane can cause a large number of aerodynamic problems, which are represented by the reduction of lift-drag ratio, the increase of flight oil consumption, the interference of static pressure system instrument indication and the serious influence on the stability and maneuverability of the airplane, and is an important risk factor threatening the service safety of aviation equipment.
The traditional deicing system such as a mixed hot air deicing system guides hot air generated in an engine to the inner side of the surface of a wing through a series of pipelines, but the design is complicated, the non-effective load of the airplane is increased, the effective thrust of the engine is reduced, and meanwhile, the thermal power density provided by the mode is limited, so that the traditional deicing system is only limited to an icing environment with a relatively mild temperature field, and the mode is not suitable for an icing environment with an extremely low temperature; the traditional air bag deicing and preventing system expands and contracts an air bag through the inflation and deflation of the air bag to generate mechanical force and mechanical vibration for deicing, but the method has high requirements on the corrosivity and the service life of materials, and has large influence on the aerodynamics of an airplane during the inflation and the inflation; the electric pulse deicing preventing system generates mechanical force with high amplitude and extremely short duration on the skin of the airplane to break and shed ice, although the deicing efficiency is high, the system enables the weight of the structure of an airplane body to be seriously increased, the deicing effect depends on the deformation size of the skin and the frequency of the pulse force, and the deicing effect on the front edge is not ideal.
The electric heating deicing technology is the mainstream deicing technology of the existing aircraft, and the metal net is laid at the position needing deicing, and when the temperature is lower than a limit, the metal net is electrified to generate heat, so that deicing is realized. The method has extremely high technical maturity, and the blade deicing system of the foreign active helicopter basically adopts an electric heating mode, but the problems of high cost, weight increment (for example, the S-76 helicopter only increases the deicing system by 150 pounds and 250 pounds), low efficiency and the like generally exist.
Along with the increase of the proportion of high-performance fiber reinforced resin matrix composite materials in airplanes and engine parts, compared with metal materials, the composite materials are poor in electric conduction and heat conduction performance and low in high-temperature resistance, a traditional electric heating mode cannot be adopted, currently, a skin is mainly used in the world, however, the skin is easily heated unevenly and the local temperature is too high due to the embedded metal mesh, meanwhile, due to the fact that the composite materials are low in heat conduction coefficient, the outer layer temperature is still in a low state due to the fact that the inner layer temperature is high, mechanical damage of thermal damage to the middle layer of the skin is caused, and the preparation of the metal pad is greatly limited by a forming process.
Disclosure of Invention
In view of the above, in order to solve at least one technical problem in the prior art, the invention provides a graphene composite film for deicing, a composite material structural member and a preparation method.
The graphene composite film for preventing and removing ice can realize rapid and uniform electric heating temperature rise and has the characteristics of softness, thinness and thinness.
The composite material structural member containing the graphene composite film and having the anti-icing and deicing functions and the preparation method thereof have the advantages that the graphene composite film can be stably combined with a composite material matrix, the thermal damage of electric heating to the composite material is reduced, and the anti-icing and deicing functions are stably realized under the condition that the mechanical property of the composite material matrix and the design requirements of an airplane are not influenced.
The graphene composite film for deicing includes: insulating layer, graphite alkene electrical heating rete, insulating heat-conducting layer, wherein:
the insulating layer is made of one or more of heat-resistant resin materials such as heat-resistant rubber, polyimide, aramid fiber, polyester, polyethylene, polypropylene and the like, and the thickness of the insulating layer is 0.01-0.50 mm; the insulating layer has the function of reducing the thermal damage of the composite material matrix caused by electric heating.
The graphene electric heating film layer mainly comprises a graphene composite film and an electrode. The thickness of the graphene composite film is 0.01-0.50mm, and the graphene composite film can be prepared from a graphene solution through processes of suction filtration, spraying, spin coating and the like, or can be obtained through chemical vapor deposition. The thickness of the electrode is 0.005-0.2mm, and the electrode can be prepared by bonding, spraying, electro-deposition, 3D printing and other modes of metals or alloys such as silver, copper, gold, aluminum, nickel and the like; the electrodes may be connected to a power source via wires.
The insulating heat-conducting layer is filled with high heat-conducting ceramic particles (AlN and Al)2O3、SiC、SiO2、Si3N4One or more of BN and diamond powder) with the thickness of 0.01-0.50mm, the content of high-thermal-conductivity ceramic particles of 1-60 vol%, the particle size of the high-thermal-conductivity ceramic particles of 0.1-100 mu m, and the addition of the high-thermal-conductivity ceramic particles can improve the thermal conductivity coefficient of the insulating heat-conducting layer; the insulating heat-conducting layer can conduct the heat of the graphene electric heating film layer to the ice layer more quickly and efficiently, and deicing efficiency and an anti-icing effect are improved.
The composite material structural member with the anti-icing and anti-icing functions comprises a composite material matrix, a graphene composite film and an adhesive film or adhesive, wherein an insulating and heat-insulating layer of the graphene composite film is adjacent to the composite material matrix; the composite material matrix is fiber reinforced resin matrix composite material, and the adhesive film or adhesive is epoxy resin adhesive film or adhesive, polyurethane adhesive film or adhesive.
The preparation method of the composite material structural member with the deicing function can be realized by adopting a secondary gluing forming method, and the specific preparation steps comprise: the method comprises the following steps: sequentially overlapping and laying an insulating heat-insulating layer, a graphene electric heating film layer and an insulating heat-conducting layer, laying an adhesive film or coating an adhesive between the insulating heat-insulating layer and the graphene electric heating film layer, and the graphene electric heating film layer and the insulating heat-conducting layer, heating to 25-100 ℃ and curing for 1-24 hours; step two: and pasting the cured glue film for the anti-icing and deicing graphene composite film on the surface of the composite material structure to realize the connection of the composite material structure layer and the graphene composite film.
The composite material structural member prepared by the secondary cementing forming method has the advantages that: the anti-icing layer is independently prepared according to the size and the shape of the composite material structure, the original preparation process and the structural performance of the composite material structure are not influenced, and the adaptability is strong.
The preparation method of the composite material structural member with the deicing function can also be realized by adopting a co-curing integral forming method, and the specific preparation steps comprise: the method comprises the following steps: after the prepreg of the composite material structure is laid and attached, an insulating thermal insulation layer, a graphene electrical heating film layer and an insulating heat conduction layer are sequentially laid on the outermost layer, and an adhesive is coated between the insulating thermal insulation layer and the graphene electrical heating film layer and between the graphene electrical heating film layer and the insulating heat conduction layer; step two: and co-curing the composite material structure layer and the graphene composite film according to a curing process of the composite material structure to form a whole, so that the composite material structure layer is connected with the graphene composite film.
The composite material structural member prepared by adopting the co-curing integral forming method has the advantages that: the molding of the graphene composite film and the molding of the composite material structure layer are realized at one time, so that the preparation procedures can be reduced, and the preparation time can be shortened.
According to the graphene composite film for preventing and removing ice, provided by the invention, the graphene is used as the electric heating film, so that the graphene composite film has better thermal stability, extremely high thermal conductivity and processing formability, and can realize rapid and uniform electric heating temperature rise; the graphene composite film further comprises an insulating and heat-conducting layer and has the characteristics of softness, thinness and thinness.
According to the composite material structural member adopting the graphene composite film, the insulating and heat-insulating layer can be stably combined with the composite material matrix, so that the heat damage of electric heating to the composite material is reduced, and the mechanical property of the composite material matrix and the design requirement of an airplane are not influenced; the graphene electric heating film is connected with a power supply system through electrodes, wires and the like, and after the graphene electric heating film is electrified, an ice layer attached to the surface of the composite material structural member can be melted through heating of the graphene composite film, so that an anti-icing and anti-icing function is realized; the insulating heat-conducting layer can conduct the heat of the graphene electric heating film layer to the surface of the composite material structural member more quickly and efficiently, and the deicing efficiency and the anti-icing effect are improved. Therefore, the composite material structural member adopting the graphene composite film can stably and efficiently realize the deicing function under the condition of not influencing the mechanical property of the composite material matrix and the design requirement of an airplane.
The composite material structural member adopting the graphene composite film is used for an airplane, particularly an airplane flying under an icing meteorological condition, such as the surfaces of transparent members of wings, a horizontal tail wing, a vertical tail wing front edge, an engine air inlet lip, an air inlet part (guide blade, support and the like), a propeller blade, a fairing, a windshield, a cabin cover and the like and the surfaces of atmospheric data detection devices such as an airspeed head, an attack angle, a temperature sensor and the like, and not only the oil consumption of airplane flying is reduced through effective ice prevention and removal, the accurate indication of an instrument is ensured, and the flying stability of the airplane is improved; the device can also be used in other devices such as wind power blades and the like used under icing meteorological conditions, and particularly the devices have the parts with the ice prevention and removal requirements.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic view of a composite structural member having an anti-icing function according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features and illustrative embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method set forth below, but rather covers any improvements, substitutions and modifications in structure, method, and apparatus without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
It should be noted that, in the case of conflict, the embodiments and features of the embodiments of the present invention may be combined with each other, and the respective embodiments may be mutually referred to and cited. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
In order to meet the design requirements of light weight, high efficiency and high aerodynamic streamline of modern composite material airplanes, the novel carbon-based electric heating material replaces the traditional metal electric heating element, the weight of an anti-icing and deicing system can be reduced, the energy consumption of the anti-icing and deicing system is reduced, the novel carbon-based electric heating material has good integration with the front edge of the wing with small curvature, the process adaptability is good, and the novel carbon-based electric heating material can be integrally formed with the composite material. The graphene has excellent force, thermal and electrical properties, the Young modulus can reach 1100GPa, the breaking strength can reach 125GPa, the thermal conductivity can reach 5000W/(mK), and the electrical conductivity can reach 10000S/cm. The graphene polymer composite membrane prepared by mixing graphene and a polymer material has the characteristics of high flexibility, high conductivity, uniform surface heating and the like, and is partially applied to electrothermic products such as electrothermic clothes, heating floors, heating paintings and the like.
In some embodiments, a method of making a composite structural member having anti-icing functionality may comprise:
1. aramid cloth with the thickness of 0.5mm is selected as an insulating layer.
2. The graphene electric heating film is an electric heating layer, the graphene composite film is prepared by vacuum filtration, the thickness of the graphene composite film is 0.10mm, and copper foil preparation electrodes with the thickness of 0.02mm are adhered to two ends of graphene by conductive adhesive.
3. AlN powder having a particle size D50 of 20 μm was mixed with polyimide to prepare an insulating and heat-conducting layer, the AlN powder content was 20 vol%, and the thickness of the polyimide film obtained was 0.1 mm.
4. Sequentially overlapping and laying aramid fabric, a graphene electric heating film layer and a polyimide film containing AlN powder, coating a polyurethane adhesive between the layers, and standing at room temperature for 24 hours to obtain the graphene composite film for preventing and removing ice;
5. and pasting the cured graphene composite film on the surface of the composite material structure by using an adhesive film.
6. The graphene composite film is connected with a power supply system through an electrode and a lead, and an ice layer attached to the surface of the graphene composite film can be melted by heating after electrification.
In some embodiments, a method of making a composite structural member having anti-icing functionality may comprise:
1. a polyimide film with the thickness of 0.1mm is selected as an insulating and heat-insulating layer.
2. The graphene electric heating film is an electric heating layer, the graphene composite film is prepared by chemical vapor deposition, the thickness of the graphene composite film is 0.20mm, and the electrodes with the thickness of 0.03mm are prepared by spraying aluminum on two ends of graphene.
3. An insulating and heat conducting layer was prepared by mixing a SiC powder having a particle size D50 of 30 μm with a polyimide, the AlN powder content was 50 vol%, and the thickness of the polyimide film obtained was 0.3 mm.
4. Sequentially overlapping and laying a carbon fiber reinforced epoxy resin prepreg layer with a composite material structure, a polyimide film, a graphene electric heating film layer and a polyimide film containing SiC powder, and coating an epoxy resin adhesive between the polyimide film and the graphene electric heating film layer and between the graphene electric heating film layer and the polyimide film containing SiC powder.
5. And co-curing the composite material structure layer and the ice prevention and removal layer into a whole according to the curing process of the composite material structure.
6. The graphene composite film is connected with a power supply system through an electrode and a lead, and an ice layer attached to the surface of the graphene composite film can be melted by heating after electrification.
In some embodiments, a method of making a composite structural member having anti-icing functionality may comprise:
1. a polypropylene film with the thickness of 0.2mm is selected as an insulating and heat-insulating layer.
2. The graphene electric heating film is an electric heating layer, the graphene composite film is prepared by chemical vapor deposition, the thickness of the graphene composite film is 0.20mm, and nickel electrodes with the thickness of 0.1mm are prepared at two ends of graphene by a 3D printing method.
3. BN powder with the particle size D50 of 10 microns is mixed with polyester to prepare an insulating heat conduction layer, the content of the BN powder is 30 vol%, and the thickness of the prepared polyester film is 0.2 mm.
4. Sequentially overlapping and laying a polypropylene film, a graphene electric heating film layer and a polyester film containing BN powder, laying an epoxy resin adhesive film between the layers, and keeping the temperature at 80 ℃ for 2 hours to obtain the graphene composite film for preventing and removing ice;
5. and pasting the cured graphene composite film on the surface of the composite material structure by using an adhesive film.
6. The graphene composite film is connected with a power supply system through an electrode and a lead, and an ice layer attached to the surface of the graphene composite film can be melted by heating after electrification.
Fig. 1 is a schematic view of a composite structural member having an anti-icing function according to an embodiment of the present invention.
As shown in fig. 1, a graphene composite film for ice control may include: insulating heat-conducting layer (10), graphite alkene electrical heating rete (20) and insulating thermal-insulating layer (30). Wherein: the graphene electric heating film layer (20) is arranged between the insulating heat conduction layer (10) and the insulating heat insulation layer (30); the insulating and heat-insulating layer (10) comprises one or more of heat-resistant resin materials: heat-resistant rubber, polyimide, aramid, polyester, polyethylene, polypropylene; the graphene electrical heating film layer (20) comprises: a graphene composite film (21) and an electrode (22). Wherein: the graphene composite film (21) is attached to the surface of the graphene electric heating film layer (20); the electrodes (22) are arranged at two ends of the graphene electric heating film layer (20); the insulating heat conducting layer (30) is heat-resistant resin filled with high heat conducting ceramic particles.
In some embodiments, the insulating and heat-insulating layer has a thickness of 0.01-0.50 mm; the thickness of the graphene composite film is 0.01-0.50 mm; the thickness of the electrode is 0.005-0.2 mm; the thickness of the insulating heat conduction layer is 0.01-0.50 mm.
In some embodiments, the high thermal conductivity ceramic particles comprise AlN, Al2O3、SiC、SiO2、Si3N4One or more of BN and diamond powder; the heat-resistant resin comprises one or more of polyimide, aramid fiber, polyester, polyethylene and polypropylene.
In some embodiments, the electrode is made of silver, copper, gold, aluminum, nickel, or other metal or alloy by bonding, spraying, electrodeposition, 3D printing, or the like.
In some embodiments, the content of the high heat conductive ceramic particles in the insulating heat conduction layer (10) is 1-60 vol%, and the particle size of the high heat conductive ceramic particles is 0.1-100 μm.
With continued reference to FIG. 1, a composite structural member having anti-icing functionality may include: a composite material matrix (40) and the graphene composite film for preventing and removing ice. Wherein: the insulating and heat-insulating layer (30) is adjacent to the composite material matrix (40) so as to separate the graphene electric heating film layer (20) from the composite material matrix (40).
The graphene composite membrane (21) is attached to a composite material substrate (40) through a glue film or an adhesive, wherein: the adhesive film or adhesive is epoxy resin adhesive film or adhesive, polyurethane adhesive film or adhesive.
In some embodiments, a method of forming a composite structural member having anti-icing functionality, comprising the steps of:
adopting a secondary glue joint forming method; alternatively, a co-cure integral molding method is employed.
The secondary glue joint forming method comprises the following steps:
the method comprises the following steps: sequentially overlapping and laying an insulating heat-insulating layer, a graphene electric heating film layer and an insulating heat-conducting layer, laying an adhesive film or coating an adhesive between the insulating heat-insulating layer and the graphene electric heating film layer, and the graphene electric heating film layer and the insulating heat-conducting layer, heating to 25-100 ℃ and curing for 1-24 hours;
step two: and pasting the cured glue film for the anti-icing and deicing graphene composite film on the surface of the composite material structure to realize the connection of the composite material structure layer and the graphene composite film.
The co-curing integral forming method comprises the following steps:
the method comprises the following steps: after the prepreg of the composite material structure is laid and attached, an insulating thermal insulation layer, a graphene electrical heating film layer and an insulating heat conduction layer are sequentially laid on the outermost layer, and an adhesive is coated between the insulating thermal insulation layer and the graphene electrical heating film layer and between the graphene electrical heating film layer and the insulating heat conduction layer;
step two: and co-curing the composite material structure layer and the graphene composite film according to a curing process of the composite material structure to form a whole, so that the composite material structure layer is connected with the graphene composite film.
In some embodiments, an anti-icing graphene composite film includes: the insulating and heat-conducting layer is characterized by also comprising a graphene electric heating film layer; wherein: the insulating layer is prepared from one or more of heat-resistant resin materials such as heat-resistant rubber, polyimide, aramid fiber, polyester, polyethylene, polypropylene and the like; the graphene electric heating film layer comprises a graphene film and an electrode; the insulating heat-conducting layer is made of heat-resistant resin (one or more of polyimide, aramid fiber, polyester, polyethylene and polypropylene) filled with high-heat-conductivity ceramic particles (one or more of AlN, Al2O3, SiC, SiO2, Si3N4, BN and diamond powder), and the thickness of the insulating heat-conducting layer is 0.01-0.50 mm.
In some embodiments, the thickness of the insulating layer is 0.01-0.50 mm; the thickness of the graphene film is 0.01-0.50mm, and the thickness of the electrode is 0.005-0.2 mm; the thickness of the insulating heat conduction layer is 0.01-0.50 mm.
In some embodiments, the graphene film is prepared from a graphene solution by suction filtration, spraying, spin coating, or chemical vapor deposition.
In some embodiments, the electrode is made of silver, copper, gold, aluminum, nickel, or other metal or alloy by bonding, spraying, electrodeposition, 3D printing, or the like.
In some embodiments, the graphene composite film for deicing is provided, and the electrode is connected with a power supply through a lead.
In some embodiments, the content of the high thermal conductivity ceramic particles in the insulating and heat conducting layer is 1-60 vol%, and the particle size of the high thermal conductivity ceramic particles is 0.1-100 μm.
In some embodiments, the insulating thermal barrier layer of the graphene composite film is adjacent to the composite matrix.
In some embodiments, the composite matrix is a fiber reinforced resin based composite.
In some embodiments, the graphene composite film is attached to the composite substrate through an adhesive film or adhesive, wherein the adhesive film or adhesive is an epoxy adhesive film or adhesive, a polyurethane adhesive film or adhesive.
In some embodiments, the method for manufacturing the composite material structural member with the function of preventing and removing ice is realized by a two-time gluing forming method, and the specific preparation steps comprise: the method comprises the following steps: sequentially overlapping and laying an insulating heat-insulating layer, a graphene electric heating film layer and an insulating heat-conducting layer, laying an adhesive film or coating an adhesive between the insulating heat-insulating layer and the graphene electric heating film layer, and the graphene electric heating film layer and the insulating heat-conducting layer, heating to 25-100 ℃ and curing for 1-24 hours; step two: and pasting the cured glue film for the anti-icing and deicing graphene composite film on the surface of the composite material structure to realize the connection of the composite material structure layer and the graphene composite film.
In some embodiments, the method for manufacturing the composite structural member with the anti-icing function is realized by a co-curing integral forming method, and the specific preparation steps comprise: the method comprises the following steps: after the prepreg of the composite material structure is laid and attached, an insulating thermal insulation layer, a graphene electrical heating film layer and an insulating heat conduction layer are sequentially laid on the outermost layer, and an adhesive is coated between the insulating thermal insulation layer and the graphene electrical heating film layer and between the graphene electrical heating film layer and the insulating heat conduction layer; step two: and co-curing the composite material structure layer and the graphene composite film according to a curing process of the composite material structure to form a whole, so that the composite material structure layer is connected with the graphene composite film.
The above technical features can be combined and applied to different degrees, and for simplicity, implementation manners of various combinations are not described again, and a person skilled in the art can flexibly adjust the sequence of the above operation steps according to actual needs, or flexibly combine the above steps, and the like.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (10)
1. A graphene composite film for deicing, comprising:
insulating heat-conducting layer (10), graphite alkene electrical heating rete (20) and insulating layer (30), wherein:
the graphene electric heating film layer (20) is arranged between the insulating heat conduction layer (10) and the insulating heat insulation layer (30);
the insulating and heat-insulating layer (10) comprises one or more of heat-resistant resin materials:
heat-resistant rubber, polyimide, aramid, polyester, polyethylene, polypropylene;
the graphene electrical heating film layer (20) comprises: a graphene composite film (21) and an electrode (22), wherein:
the graphene composite film (21) is attached to the surface of the graphene electric heating film layer (20);
the electrodes (22) are arranged at two ends of the graphene electric heating film layer (20);
the insulating heat conducting layer (30) is heat-resistant resin filled with high heat conducting ceramic particles.
2. The graphene composite film for deicing according to claim 1, wherein:
the thickness of the insulating layer is 0.01-0.50 mm;
the thickness of the graphene composite film is 0.01-0.50 mm;
the thickness of the electrode is 0.005-0.2 mm;
the thickness of the insulating heat conduction layer is 0.01-0.50 mm.
3. The graphene composite film for deicing according to claim 1 or 2, wherein:
the high heat-conducting ceramic particles comprise AlN and Al2O3、SiC、SiO2、Si3N4One or more of BN and diamond powder;
the heat-resistant resin comprises one or more of polyimide, aramid fiber, polyester, polyethylene and polypropylene.
4. The graphene composite film for deicing according to claim 1 or 2, wherein:
the electrode is prepared from metals or alloys of silver, copper, gold, aluminum, nickel and the like through bonding, spraying, electrodeposition, 3D printing and the like.
5. The graphene composite film for deicing according to claim 1 or 2, wherein:
the content of the high-heat-conduction ceramic particles in the insulating heat conduction layer (10) is 1-60 vol%,
the grain diameter of the high heat conduction ceramic grains is 0.1-100 μm.
6. A composite structural member having an anti-icing function, comprising:
the composite material substrate (40) and the deicing graphene composite film according to any one of claims 1 to 5, wherein:
the insulating and heat-insulating layer (30) is adjacent to the composite material matrix (40) so as to separate the graphene electric heating film layer (20) from the composite material matrix (40).
7. The composite structural member of claim 6, wherein:
the graphene composite membrane (21) is attached to a composite material substrate (40) through a glue film or an adhesive, wherein: the adhesive film or adhesive is epoxy resin adhesive film or adhesive, polyurethane adhesive film or adhesive.
8. A method for preparing a composite structural element with anti-icing function according to claims 7 and 8, characterized in that it comprises the following steps:
adopting a secondary glue joint forming method;
alternatively, the first and second electrodes may be,
adopting a co-curing integral forming method.
9. The method of claim 8, wherein the secondary adhesive bonding comprises:
the method comprises the following steps: sequentially overlapping and laying an insulating heat-insulating layer, a graphene electric heating film layer and an insulating heat-conducting layer, laying an adhesive film or coating an adhesive between the insulating heat-insulating layer and the graphene electric heating film layer, and the graphene electric heating film layer and the insulating heat-conducting layer, heating to 25-100 ℃ and curing for 1-24 hours;
step two: and pasting the cured glue film for the anti-icing and deicing graphene composite film on the surface of the composite material structure to realize the connection of the composite material structure layer and the graphene composite film.
10. The method of claim 8, wherein using a co-cure one-piece process comprises:
the method comprises the following steps: after the prepreg of the composite material structure is laid and attached, an insulating thermal insulation layer, a graphene electrical heating film layer and an insulating heat conduction layer are sequentially laid on the outermost layer, and an adhesive is coated between the insulating thermal insulation layer and the graphene electrical heating film layer and between the graphene electrical heating film layer and the insulating heat conduction layer;
step two: and co-curing the composite material structure layer and the graphene composite film according to a curing process of the composite material structure to form a whole, so that the composite material structure layer is connected with the graphene composite film.
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