CN111204063A - Curing method and curing system of glass fiber reinforced resin matrix composite - Google Patents

Curing method and curing system of glass fiber reinforced resin matrix composite Download PDF

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CN111204063A
CN111204063A CN202010210222.1A CN202010210222A CN111204063A CN 111204063 A CN111204063 A CN 111204063A CN 202010210222 A CN202010210222 A CN 202010210222A CN 111204063 A CN111204063 A CN 111204063A
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graphene
reinforced resin
composite material
curing
fiber
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钟勉
李军辉
张华忠
胡焱
秦文峰
徐亚军
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Civil Aviation Flight University of China
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Civil Aviation Flight University of China
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/18—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated tools
    • B29C65/24—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure using heated tools characterised by the means for heating the tool
    • B29C65/30—Electrical means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/02—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by heating, with or without pressure
    • B29C65/44—Joining a heated non plastics element to a plastics element

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  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Health & Medical Sciences (AREA)
  • Oral & Maxillofacial Surgery (AREA)
  • Reinforced Plastic Materials (AREA)
  • Compositions Of Macromolecular Compounds (AREA)

Abstract

The invention relates to the field of composite material curing, and particularly provides a curing method and a curing system for a glass fiber reinforced resin matrix composite material. A method of curing a fibre reinforced resin based composite material comprising: and arranging the fiber reinforced resin matrix composite material to be cured on at least one side of the graphene material, and then electrically heating the graphene material. In the curing method, after the graphene material is electrically heated, the graphene material starts to generate heat, the heat is transferred to the fiber reinforced resin matrix composite material to be cured on at least one side of the graphene material, and the composite material is cured by utilizing the heat. The method can effectively improve the curing efficiency of the fiber reinforced resin matrix composite material, does not need to use large-scale equipment such as an oven and the like to cure the fiber reinforced resin matrix composite material, has low economic cost, has stable chemical properties of the graphene material, can be recycled, further reduces the curing cost, and is more environment-friendly.

Description

Curing method and curing system of glass fiber reinforced resin matrix composite
Technical Field
The invention relates to the field of composite material curing, in particular to a curing method and a curing system for a glass fiber reinforced resin matrix composite material.
Background
Glass fiber reinforced resin-based composite materials have the advantages of high specific strength, good fatigue resistance, excellent design and the like, and therefore, glass fiber reinforced resin-based composite materials are increasingly applied to many fields, particularly structures or components sensitive to weight and environment, such as land vehicles, airplanes and the like.
The excellent structural performance of the glass fiber reinforced resin matrix composite material is related to the curing effect of the glass fiber resin prepreg, at present, the glass fiber resin prepreg is cured in an oven, the final curing effect is influenced by the pressure and the temperature during curing, in the curing process, a great amount of energy is firstly needed to increase the temperature of the oven, and then the heat is transferred to the composite material through air. Because the oven is much larger than the composite itself, the curing process is inefficient, wasting a significant amount of time and energy; and the special oven specially manufactured for large composite material parts is also high in manufacturing cost. Therefore, these disadvantages greatly hinder the large-scale application of the composite material, especially for the maintenance of the aircraft at the outfield, and the like.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to provide a curing method of a fiber reinforced resin matrix composite, which can effectively improve the curing efficiency of the fiber reinforced resin matrix composite, and has the advantages of low manufacturing cost and environmental friendliness.
The second purpose of the invention is to provide a curing system of fiber reinforced resin matrix composite material, which has the advantages of higher curing efficiency, simple structure and lower manufacturing cost and is suitable for large-scale application.
A third object of the present invention is to provide a fiber reinforced resin based composite material cured by the above curing method and/or curing system.
A fourth object of the present invention is to provide a use of the above-mentioned curing method and/or curing system in aircraft maintenance.
A fifth object of the invention is to provide an aircraft component or an aircraft.
In order to achieve the above purpose of the present invention, the following technical solutions are adopted:
in a first aspect, the present invention provides a method for curing a fiber reinforced resin based composite material, comprising: and arranging the fiber reinforced resin matrix composite material to be cured on at least one side of the graphene material, and then electrically heating the graphene material.
As a further preferable aspect, the electrical heating includes: firstly, heating the graphene material to 90-98 ℃, preserving heat for 0.1-1h, then continuously heating to 115-125 ℃, and preserving heat for 1-2 h.
As a further preferred technical scheme, after a heat conduction isolation material is inserted between the fiber reinforced resin matrix composite material to be cured and the graphene material, the graphene material is electrically heated;
preferably, the heat-conducting isolating material comprises polytetrafluoroethylene, heat-conducting silica gel, heat-conducting double-sided adhesive or aluminum alloy;
preferably, the thickness of the heat-conducting isolating material is 5-10 mm.
As a further preferable technical solution, the graphene-based material includes graphene;
preferably, the graphene-based material has an areal density of 4.5 to 5.5g/m2；
Preferably, the graphene-based material has a thickness of 15-25 μm;
preferably, the graphene-based material has an electrical conductivity of 4.0 × 104～4.5×104S/m。
As a further preferred technical scheme, the fiber reinforced resin matrix composite material to be cured comprises the following components: fibers, resins and curing agents;
preferably, the resin comprises an epoxy resin, more preferably a Cycom970 epoxy resin or an EH103 epoxy resin;
preferably, the fibers comprise glass fibers;
preferably, the weight ratio of the fiber, the resin and the curing agent is (65-70): (22-28): (3-8);
preferably, the fibers have an areal density of 200-250g/m2。
In a second aspect, the present invention provides a curing system for a fibre reinforced resin based composite material, comprising:
a fiber reinforced resin based composite material layer to be cured;
the graphene material layer is arranged on at least one side of the composite material layer and is connected with a power supply.
As a further preferable technical scheme, a heat conduction isolation layer is further arranged between the composite material layer and the graphene material layer;
preferably, the material of the graphene-based material layer comprises graphene;
preferably, the thickness of the graphene-based material layer is 15-25 μm;
preferably, the thickness of the heat conduction isolation layer is 5-10 mm;
preferably, the material of the heat-conducting isolation layer comprises polytetrafluoroethylene, heat-conducting silica gel, heat-conducting double-sided adhesive or aluminum alloy;
preferably, both ends of the graphene-based material layer are respectively connected with a positive electrode and a negative electrode, and the graphene-based material layer is connected with the power supply through the positive electrode and the negative electrode;
preferably, the positive electrode and/or the negative electrode comprises a copper tube electrode;
preferably, a conductive silver paste is disposed between each of the positive electrode and the negative electrode and the graphene-based material layer.
In a third aspect, the invention provides a fiber reinforced resin matrix composite obtained by curing the curing method of the fiber reinforced resin matrix composite and/or the curing system of the fiber reinforced resin matrix composite.
In a fourth aspect, the invention provides a method for curing the fiber reinforced resin matrix composite material and/or an application of the curing system of the fiber reinforced resin matrix composite material in aircraft maintenance.
In a fifth aspect, the present invention provides an aircraft component comprising the above fibre-reinforced resin-based composite material;
or, an aircraft comprising the above fiber reinforced resin based composite material.
Compared with the prior art, the invention has the beneficial effects that:
according to the curing method of the fiber reinforced resin matrix composite material, the graphene material is used for curing the fiber reinforced resin matrix composite material, after the graphene material is electrically heated, the graphene material starts to generate heat, the heat is transferred to the fiber reinforced resin matrix composite material to be cured on at least one side of the graphene material, and the composite material is cured by utilizing the heat. The method can effectively improve the curing efficiency of the fiber reinforced resin matrix composite material, does not need to use large-scale equipment such as an oven and the like to cure the fiber reinforced resin matrix composite material, has low manufacturing cost, has stable chemical properties of the graphene material, can not be degraded after heating, can be recycled, further reduces the curing cost, and is more environment-friendly.
The curing system provided by the invention cures the fiber reinforced resin matrix composite material layer to be cured by adopting the graphene material layer, heats the graphene material layer after the electric quantity of the power supply is transmitted to the graphene material layer, and diffuses and radiates the heat of the graphene material layer to the composite material layer, thereby realizing the curing of the composite material layer. In the curing system, the heat of the graphene material layer is directly transferred to the composite material layer to be cured, so that the waste of time and energy caused by the fact that the air needs to be heated and then cured in a traditional oven is avoided, and the curing efficiency is higher; in addition, the curing system has simple structure and lower manufacturing cost, and is suitable for large-scale application.
Drawings
Fig. 1 is a schematic diagram of the change of the temperature of a graphene film with curing time;
FIG. 2 is a schematic diagram showing the change of the surface temperature of the graphene film with time under different heating voltages;
FIG. 3 is a schematic structural diagram of a curing system for an embodiment of a fiber reinforced resin based composite material.
Icon: 1-a fiber reinforced resin based composite material layer to be cured; a layer of 2-graphene-based material; 3-a power supply; 4-heat conducting isolation layer; 5-a positive electrode; 6-negative electrode.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to examples, but it will be understood by those skilled in the art that the following examples are only illustrative of the present invention and should not be construed as limiting the scope of the present invention. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer.
According to one aspect of the present invention, there is provided a method of curing a fibre reinforced resin based composite material, comprising: and arranging the fiber reinforced resin matrix composite material to be cured on at least one side of the graphene material, and then electrically heating the graphene material.
The graphene material has excellent mechanical properties, physical and chemical stability, thermal stability, good electric and heat conduction and other properties, when current passes through the graphene material, the graphene material can be rapidly heated, and heat is diffused to the surrounding environment through radiation. According to the method, the fiber reinforced resin matrix composite material is cured by the graphene material, the graphene material starts to generate heat after the graphene material is electrically heated, the heat is transferred to the fiber reinforced resin matrix composite material to be cured on at least one side of the graphene material, and the composite material is cured by the heat. The method can effectively improve the curing efficiency of the fiber reinforced resin matrix composite material, does not need to use large-scale equipment such as an oven and the like to cure the fiber reinforced resin matrix composite material, has low manufacturing cost, has stable chemical properties of the graphene material, can be recycled, further reduces the curing cost, and is more environment-friendly.
It should be noted that:
the "fiber reinforced resin matrix composite material" refers to a fiber reinforced material using an organic polymer as a matrix, and includes, but is not limited to, a glass fiber reinforced resin matrix composite material, a carbon fiber reinforced resin matrix composite material, a basalt fiber reinforced resin matrix composite material, or an aramid fiber reinforced resin matrix composite material.
The above-mentioned "fiber-reinforced resin-based composite material to be cured" may also be referred to as a fiber resin-reinforced resin-based composite material prepreg.
The "graphene-based material" refers to graphene and/or a graphene derivative. "graphene derivative" refers to a substance obtained by modifying graphene by methods including, but not limited to, oxidation, hydrogenation, fluorination, organic functionalization, or covalent and non-covalent modification of graphene by a polymer, and the like. Graphene derivatives include, but are not limited to, graphene oxide or graphene fluoride, and the like.
The graphene-based material may be disposed on one side or both sides of the graphene-based material.
In a preferred embodiment, the graphene-based material comprises graphene. Compared with graphene derivatives, the graphene has better electrical properties and better heating effect, thereby being more beneficial to curing of composite materials and improving curing efficiency.
In a preferred embodiment, after the thermal conductive insulating material is inserted between the fiber reinforced resin matrix composite material to be cured and the graphene-based material, the graphene-based material is electrically heated. The heat conduction isolating material can not only transfer heat generated by the graphene materials to the composite material, but also isolate the composite material from the graphene materials, so that the pollution of the uncured composite material to the graphene materials is avoided, and the reutilization rate of the graphene materials is improved.
Preferably, the heat-conducting isolation material comprises polytetrafluoroethylene, heat-conducting silica gel, heat-conducting double-sided adhesive or aluminum alloy. The polytetrafluoroethylene, the heat-conducting silica gel, the heat-conducting double-sided adhesive or the aluminum alloy has stable chemical properties and good isolation effect and is not adhered to the resin matrix. The heat-conducting insulating material can be selected to be in a sheet shape or a belt shape.
Preferably, the thickness of the heat-conducting isolating material is 5-10 mm. The thickness of the heat-conducting isolating material is not too large or too small, the isolating effect is poor when the thickness is too small, and the heat-conducting effect is poor when the thickness is too large. The thickness gives consideration to heat conduction and isolation, and is more suitable for practical application. Such thicknesses are typically, but not limited to, 5mm, 5.5mm, 6mm, 6.5mm, 7mm, 7.5mm, 8mm, 8.5mm, 9mm, 9.5mm, or 10 mm.
In a preferred embodiment, the graphene-based material has an areal density of 4.5 to 5.5g/m2. When the surface density of the graphene material is 4.5-5.5g/m2In the process, the number of carbon atoms in a unit area is reasonable, and the electrical conductivity of the graphene material is reasonable, so that the conductive graphene material is beneficial to heat generation and heat conduction after the electrical conductivity is improved. The above areal density is typically, but not limited to, 4.1, 4.2, 4.3, 4.4, 4.5, 4.6, 4.7, 4.8, 4.9 or 5g/m2。
Preferably, the graphene-based material has a thickness of 15 to 25 μm. The thickness of the graphene material is not too large or too small, and the thickness is too small, so that the heat stored in the graphene material is insufficient, and the composite material cannot be effectively cured; the thickness is too large, which not only increases energy consumption, but also does not make the curing effect better and the manufacturing cost higher. The above thickness is typically, but not limited to, 15 μm, 16 μm, 17 μm, 18 μm, 19 μm, 20 μm, 21 μm, 22 μm, 23 μm, 24 μm or 25 μm.
Preferably, the graphene-based material has an electrical conductivity of 4.0 × 104～4.5×104And (5) S/m. When the conductivity of the graphene material is 4.0 x 104～4.5×104And when the graphene is in an S/m state, the conductive effect is good, the rapid heating of the graphene material can be realized, and the curing efficiency is improved. The above conductivity is typically, but not limited to, 4.0X 104S/m、4.1×104S/m、4.2×104S/m、4.3×104S/m、 4.4×104S/m or 4.5X 104S/m。
In a preferred embodiment, the electrical heating comprises: firstly, heating the graphene material to 90-98 ℃, preserving heat for 0.1-1h, then continuously heating to 115-125 ℃, and preserving heat for 1-2 h. The temperature of the above first heating is typically, but not limited to, 90, 91, 92, 93, 94 or 95 ℃, and the first incubation time is typically, but not limited to, 0.1, 0.2, 0.3, 0.4, 0.5, 0.6, 0.7, 0.8, 0.9 or 1 hour; the temperature at which heating is continued is typically, but not limited to, 115, 116, 117, 118, 119, 120, 121, 122, 123, 124 or 125 deg.C, and the second incubation time is typically, but not limited to, 1, 1.1, 1.2, 1.3, 1.4, 1.5, 1.6, 1.7, 1.8, 1.9 or 2 hours.
In the preferred embodiment, the graphene material is firstly insulated for a certain time at a lower temperature, and the composite material to be cured is preheated at the lower temperature through heat transfer; then the graphene material is kept warm for a certain time at a higher temperature, and the composite material to be cured is cured at a higher temperature through heat transfer. Compared with the mode of directly heating to a higher temperature for curing, the composite material obtained by curing in the preferred embodiment has better mechanical properties.
Optionally, the graphene material is heated to 90-98 ℃ by adopting direct current of 5V and 1.75A, and the current is increased to continue heating to 115-125 ℃ after heat preservation.
As shown in fig. 1, the temperature of the graphene film changes with the curing time, and it can be seen from the figure that the graphene film undergoes two temperature increases, and platforms appear at 95 ℃ and 120 ℃ respectively, which indicates that the graphene film is a heat preservation section, and then the temperature is reduced.
Fig. 2 shows the surface temperature of the graphene film with time under different heating voltages, and it can be seen from the graph that the surface temperature of the graphene film is the highest when the heating voltage is 5V.
In a preferred embodiment, the fiber reinforced resin based composite material to be cured comprises the following components: fibers, resins and curing agents;
preferably, the resin comprises an epoxy resin, more preferably a Cycom970 epoxy resin or an EH103 epoxy resin;
preferably, the fibers comprise glass fibers;
preferably, the weight ratio of the fiber, the resin and the curing agent is (65-70): (22-28): (3-8). Typical but not limiting ratios are 69:25:6, 65:22:3, 70:25:5, 68:28:8, 65:28:8 or 70:22: 3.
Preferably, the fibers have an areal density of 200-250g/m2. The above areal density is typically, but not limited to, 200, 210, 220, 224, 230, 240 or 250g/m2。
The fiber reinforced resin matrix composite to be cured in the preferred embodiment has scientific and reasonable composition, the curing effect of the composite material is better than that of other composite materials, and the mechanical property of the obtained composite material is more excellent.
Optionally, the method further comprises the step of connecting a positive electrode and a negative electrode at two ends of the graphene material, and then arranging the fiber reinforced resin matrix composite material to be cured on one side of the graphene material.
Optionally, the electrode comprises a copper tube electrode.
Optionally, a conductive silver paste is used to connect the graphene-based material to the positive and negative electrodes.
According to another aspect of the present invention, as shown in fig. 3, there is provided a curing system for a fiber reinforced resin based composite material, comprising: a fiber reinforced resin matrix composite layer 1 to be cured; the graphene-based material layer 2 is arranged on at least one side of the fiber reinforced resin-based composite material layer 1 to be cured, and the graphene-based material layer 2 is connected with the power supply 3.
The graphene material has excellent mechanical properties, physical and chemical stability, thermal stability, good electric and heat conduction and other properties, when current passes through the graphene material, the graphene material can be rapidly heated, and heat is diffused to the surrounding environment through radiation.
The curing system provided by the invention cures the fiber reinforced resin matrix composite material layer to be cured by adopting the graphene material layer, heats the graphene material layer after the electric quantity of the power supply is transmitted to the graphene material layer, and diffuses and radiates the heat of the graphene material layer to the composite material layer, thereby realizing the curing of the composite material layer. In the curing system, the heat of the graphene material layer is directly transferred to the composite material layer to be cured, so that the waste of time and energy caused by the fact that the air needs to be heated and then cured in a traditional oven is avoided, and the curing efficiency is higher; in addition, the curing system has simple structure and lower manufacturing cost, and is suitable for large-scale application.
It should be noted that:
the "fiber reinforced resin matrix composite material" refers to a fiber reinforced material using an organic polymer as a matrix, and includes, but is not limited to, a glass fiber reinforced resin matrix composite material, a carbon fiber reinforced resin matrix composite material, a basalt fiber reinforced resin matrix composite material, or an aramid fiber reinforced resin matrix composite material.
The above-mentioned "fiber-reinforced resin-based composite material layer to be cured" is mainly formed of a fiber-reinforced resin-based composite material to be cured.
The "graphene-based material layer" refers to a layered structure formed of graphene and/or a graphene derivative. "graphene derivative" refers to a substance obtained by modifying graphene by methods including, but not limited to, oxidation, hydrogenation, fluorination, organic functionalization, or covalent and non-covalent modification of graphene by a polymer, and the like. Graphene derivatives include, but are not limited to, graphene oxide or graphene fluoride, and the like.
In a preferred embodiment, a thermal insulation layer 4 is further included between the fiber reinforced resin based composite material layer 1 to be cured and the graphene based material layer 2. The heat conduction isolation layer not only can be with the heat transfer to the combined material layer that the graphite alkene material layer produced, can also keep apart combined material layer and graphite alkene material layer, avoids the combined material that still does not solidify to cause the pollution to graphite alkene material layer, improves the reuse rate of graphite alkene material layer.
Preferably, the material of the graphene-based material layer includes graphene.
Preferably, the graphene-based material layer has a thickness of 15 to 25 μm.
Preferably, the thickness of the heat conduction isolation layer is 5-10 mm.
Preferably, the material of the heat conduction isolation layer comprises polytetrafluoroethylene, heat conduction silica gel, heat conduction double faced adhesive tape or aluminum alloy.
Preferably, the graphene-based material layer 2 is connected with a positive electrode 5 and a negative electrode 6 at two ends thereof, respectively, and the graphene-based material layer 2 is connected with the power source 3 through the positive electrode 5 and the negative electrode 6.
Preferably, the positive electrode and/or the negative electrode comprise copper tube electrodes. The copper tube electrode has better conductivity compared with other electrodes, can effectively transfer the electric quantity generated by a power supply to the graphene material layer, reduces the heat loss of the electric quantity at the electrode, improves the energy utilization rate, and further reduces the cost.
Preferably, a conductive silver paste (not shown) is disposed between each of the positive electrode and the negative electrode and the graphene-based material layer. The conductive silver paste can enable the positive electrode and the negative electrode to form good electric contact with the graphene material layer.
According to another aspect of the invention, a curing method of the fiber-reinforced resin-based composite material and/or a fiber-reinforced resin-based composite material obtained by curing by using the curing system of the fiber-reinforced resin-based composite material are provided. The fiber reinforced resin matrix composite material has the advantages of good mechanical property and low cost.
According to a further aspect of the invention there is provided the use of a curing method as described above and/or a curing system as described above in aircraft servicing. The curing method and/or the curing system are applied to aircraft maintenance, so that the aircraft maintenance efficiency can be improved, and the maintenance cost can be reduced.
The "aircraft maintenance" refers to maintenance and repair of various components, equipment or parts of the aircraft to ensure safe sailing.
According to a further aspect of the present invention there is provided an aircraft component or aircraft comprising a fibre-reinforced resin-based composite material as described above. The aircraft component or aircraft has at least the same advantages as the composite material, and has the advantages of good mechanical property and low cost.
The term "aircraft component" as used herein refers to various components that make up an aircraft, including, but not limited to, wings, fuselage, tail or landing gear, etc.
The present invention will be described in further detail with reference to examples and comparative examples.
Example 1
A method of curing a fibre reinforced resin based composite material comprising: arranging a fiber reinforced resin matrix composite material to be cured on one side of graphene oxide, and then electrically heating the graphene oxide;
the electrical heating comprises: heating the graphene oxide to 120 ℃, and preserving heat for 2 hours;
the surface density of the graphene oxide is 200g/m2(ii) a Thickness of 15 μm and conductivity of 4.0 × 104S/m。
The fiber reinforced resin matrix composite material to be cured comprises the following components: the fiber comprises carbon fiber, the resin comprises phenolic resin, the curing agent comprises WHUT-Esys 208B (provided by Wuhan university of science), the weight ratio of the fiber to the resin to the curing agent is 65:22:3, and the areal density of the fiber is 200g/m2。
Example 2
Unlike example 1, in the present example, the electrical heating includes: firstly, heating the graphene material to 95 ℃, preserving heat for 0.5h, then continuously heating to 120 ℃, and preserving heat for 1.5 h. The rest is the same as in example 1.
Example 3
Different from embodiment 2, in the present embodiment, graphene oxide is replaced with graphene.
Example 4
Different from the embodiment 3, in the embodiment, the surface density of the graphene is 4.99g/m2。
Example 5
Different from the embodiment 4, the curing method of the fiber reinforced resin matrix composite material is that the thickness of graphene is 20 microns in the embodiment.
Example 6
Different from the embodiment 5, in the embodiment, the conductivity of the graphene is 4.38 multiplied by 104S/m。
Example 7
A method of curing a fibre reinforced resin based composite material, which differs from example 6 in that the fibres comprise glass fibres.
Example 8
A method of curing a fiber-reinforced resin-based composite material, which differs from embodiment 7 in that the resin comprises an epoxy resin.
Example 9
Different from the embodiment 8, the weight ratio of the fiber, the resin and the curing agent is 69:25: 6.
Example 10
A curing method of a fiber reinforced resin matrix composite material is different from the embodiment 9 in that the surface density of the fiber is 224g/m2。
Example 11
A method for curing a fiber-reinforced resin-based composite material, which is different from embodiment 10, in this embodiment, after a thermal conductive isolation material is inserted between a fiber-reinforced resin-based composite material to be cured and graphene, the graphene-based material is electrically heated; the heat conduction isolation material is polyethylene, and the thickness of the heat conduction isolation material is 10 mm.
Example 12
A method for curing a fiber reinforced resin-based composite material, which is different from embodiment 11 in that the thermal conductive isolation material is polytetrafluoroethylene.
Example 13
Different from the embodiment 12, the curing method of the fiber reinforced resin matrix composite material is that the thickness of the heat-conducting insulating material is 8 mm.
Example 14
Different from embodiment 2, in the present embodiment, graphene oxide is replaced with graphene fluoride.
Example 15
Different from embodiment 1, in the embodiment, the fiber reinforced resin matrix composite to be cured is arranged on two sides of graphene oxide.
Comparative example 1
The curing method of the fiber reinforced resin matrix composite material is different from the embodiment 1 in that an oven is adopted for heating and curing the fiber reinforced resin matrix composite material to be cured, the temperature of the oven is 80 ℃, and the curing time is 150 min.
Comparative example 2
The curing method of the fiber reinforced resin matrix composite material is different from the embodiment 1 in that an autoclave is adopted to heat and cure the fiber reinforced resin matrix composite material to be cured, the temperature of the autoclave is 120 ℃, the pressure is 0.6MPa, and the curing time is 80 min.
Comparative example 3
The curing method of the fiber reinforced resin matrix composite material is different from the embodiment 1 in that the fiber reinforced resin matrix composite material to be cured is heated and cured by adopting a heating resistor, wherein the temperature of the heating resistor is 95 ℃, and the curing time is 120 min.
The fiber reinforced resin based composite materials cured by the methods of the above examples and comparative examples were subjected to tensile strength tests (refer to GBT3354-1999 tensile Property test method for oriented fiber reinforced plastics), and the test results are shown in Table 1.
TABLE 1
Figure BDA0002421060790000141
Figure BDA0002421060790000151
The comparison of the properties of example 2, example 3 and example 14 shows that the overall properties of example 3 are the best, indicating that graphene is more effective in curing composite materials.
While particular embodiments of the present invention have been illustrated and described, it would be obvious that various other changes and modifications can be made without departing from the spirit and scope of the invention. It is therefore intended to cover in the appended claims all such changes and modifications that are within the scope of this invention.

Claims (10)

1.一种纤维增强树脂基复合材料的固化方法，其特征在于，包括：将待固化的纤维增强树脂基复合材料设置于石墨烯类材料的至少一侧，然后对石墨烯类材料进行电加热。1. a curing method of fiber-reinforced resin-based composite material, is characterized in that, comprising: the fiber-reinforced resin-based composite material to be cured is arranged on at least one side of graphene-based material, then the graphene-based material is electrically heated . 2.根据权利要求1所述的纤维增强树脂基复合材料的固化方法，其特征在于，所述电加热包括：首先将石墨烯类材料加热到90-98℃，保温0.1-1h，然后继续加热到115-125℃，保温1-2h。2 . The method for curing fiber-reinforced resin-based composite materials according to claim 1 , wherein the electric heating comprises: firstly heating the graphene-based material to 90-98° C., keeping the temperature for 0.1-1 h, and then continuing to heat. 3 . To 115-125 ℃, keep warm for 1-2h. 3.根据权利要求1所述的纤维增强树脂基复合材料的固化方法，其特征在于，在待固化的纤维增强树脂基复合材料与石墨烯类材料之间插入导热隔离材料后，再对石墨烯类材料进行电加热；3. the curing method of fiber-reinforced resin-based composite material according to claim 1, is characterized in that, after inserting thermally conductive isolation material between the fiber-reinforced resin-based composite material to be cured and the graphene-like material, then to graphene Electric heating of similar materials; 优选地，所述导热隔离材料包括聚四氟乙烯、导热硅胶、导热双面胶或铝合金；Preferably, the thermally conductive isolation material comprises polytetrafluoroethylene, thermally conductive silica gel, thermally conductive double-sided adhesive or aluminum alloy; 优选地，所述导热隔离材料的厚度为5-10mm。Preferably, the thickness of the thermally conductive insulating material is 5-10 mm. 4.根据权利要求1所述的纤维增强树脂基复合材料的固化方法，其特征在于，所述石墨烯类材料包括石墨烯；4. The curing method of fiber-reinforced resin-based composite material according to claim 1, wherein the graphene-based material comprises graphene; 优选地，石墨烯类材料的面密度为4.5-5.5g/m2；Preferably, the areal density of the graphene-based material is 4.5-5.5 g/m 2 ; 优选地，石墨烯类材料的厚度为15-25μm；Preferably, the thickness of the graphene-based material is 15-25 μm; 优选地，石墨烯类材料的电导率为4.0×104～4.5×104S/m。Preferably, the electrical conductivity of the graphene-based material is 4.0×10 4 to 4.5×10 4 S/m. 5.根据权利要求1-4任一项所述的纤维增强树脂基复合材料的固化方法，其特征在于，待固化的纤维增强树脂基复合材料包括以下组分：纤维、树脂和固化剂；5. The curing method of fiber-reinforced resin-based composite material according to any one of claims 1-4, wherein the fiber-reinforced resin-based composite material to be cured comprises the following components: fiber, resin and curing agent; 优选地，所述树脂包括环氧树脂，进一步优选为Cycom970环氧树脂或EH103环氧树脂；Preferably, the resin includes epoxy resin, more preferably Cycom970 epoxy resin or EH103 epoxy resin; 优选地，所述纤维包括玻璃纤维；Preferably, the fibers comprise glass fibers; 优选地，纤维、树脂与固化剂的重量比为(65-70):(22-28):(3-8)；Preferably, the weight ratio of fiber, resin and curing agent is (65-70):(22-28):(3-8); 优选地，纤维的面密度为200-250g/m2。Preferably, the fibers have an areal density of 200-250 g/m 2 . 6.一种纤维增强树脂基复合材料的固化系统，其特征在于，包括：6. A curing system of fiber-reinforced resin-based composite material, characterized in that, comprising: 待固化的纤维增强树脂基复合材料层；a fiber-reinforced resin matrix composite material layer to be cured; 石墨烯类材料层，所述石墨烯类材料层设置于所述复合材料层的至少一侧，且所述石墨烯类材料层与电源相连。A graphene-based material layer, the graphene-based material layer is disposed on at least one side of the composite material layer, and the graphene-based material layer is connected to a power source. 7.根据权利要求6所述的纤维增强树脂基复合材料的固化系统，其特征在于，所述复合材料层和所述石墨烯类材料层之间还包括导热隔离层；7. The curing system of the fiber-reinforced resin-based composite material according to claim 6, characterized in that, a thermally conductive isolation layer is further included between the composite material layer and the graphene-based material layer; 优选地，所述石墨烯类材料层的材质包括石墨烯；Preferably, the material of the graphene-based material layer includes graphene; 优选地，所述石墨烯类材料层的厚度为15-25μm；Preferably, the thickness of the graphene-based material layer is 15-25 μm; 优选地，所述导热隔离层的厚度为5-10mm；Preferably, the thickness of the thermally conductive isolation layer is 5-10 mm; 优选地，所述导热隔离层的材质包括聚四氟乙烯、导热硅胶、导热双面胶或铝合金；Preferably, the material of the thermally conductive isolation layer comprises polytetrafluoroethylene, thermally conductive silica gel, thermally conductive double-sided adhesive or aluminum alloy; 优选地，所述石墨烯类材料层两端分别连接有正电极和负电极，所述石墨烯类材料层通过所述正电极和所述负电极与所述电源相连；Preferably, both ends of the graphene-based material layer are respectively connected with a positive electrode and a negative electrode, and the graphene-based material layer is connected to the power source through the positive electrode and the negative electrode; 优选地，所述正电极和/或所述负电极包括铜管电极；Preferably, the positive electrode and/or the negative electrode comprises a copper tube electrode; 优选地，所述正电极和所述负电极与所述石墨烯类材料层之间均设置有导电银浆。Preferably, conductive silver paste is provided between the positive electrode and the negative electrode and the graphene-based material layer. 8.采用权利要求1-5任一项所述的纤维增强树脂基复合材料的固化方法和/或采用权利要求6或7所述的纤维增强树脂基复合材料的固化系统固化得到的纤维增强树脂基复合材料。8. The fiber reinforced resin obtained by curing using the curing method of the fiber reinforced resin matrix composite material according to any one of claims 1-5 and/or using the curing system of the fiber reinforced resin matrix composite material according to claim 6 or 7 Matrix composites. 9.权利要求1-5任一项所述的纤维增强树脂基复合材料的固化方法和/或权利要求6或7所述的纤维增强树脂基复合材料的固化系统在飞机维修中的应用。9. The application of the curing method of fiber-reinforced resin matrix composite material according to any one of claims 1 to 5 and/or the curing system of fiber-reinforced resin matrix composite material according to claim 6 or 7 in aircraft maintenance. 10.一种飞机部件，其特征在于，包括权利要求8所述的纤维增强树脂基复合材料；10. An aircraft component, characterized in that, comprising the fiber-reinforced resin-based composite material of claim 8; 或，一种飞机，包括权利要求8所述的纤维增强树脂基复合材料。Or, an aircraft comprising the fiber-reinforced resin matrix composite material of claim 8 .
CN202010210222.1A 2020-03-23 2020-03-23 Curing method and curing system of glass fiber reinforced resin matrix composite Pending CN111204063A (en)

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Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012004942A1 (en) * 2012-03-12 2013-09-12 Munich Composites Gmbh Process for producing a preform and a fiber composite prefabricated component produced therefrom
CN205022011U (en) * 2015-10-13 2016-02-10 山东柏远复合材料科技有限公司 Continuous densification of fiber reinforcement thermoset plastics pipeline, high -efficient production line
KR20160083519A (en) * 2014-12-31 2016-07-12 주식회사 삼양사 Long-fiber reinforced thermoplastic resin composition with excellent thermal conductivity and mechanical properties
CN205439290U (en) * 2016-02-26 2016-08-10 深圳市梦之坊通信产品有限公司 Combined material cell phone case's exhausted formula molding device
US20170238367A1 (en) * 2016-02-15 2017-08-17 General Electric Company Integrated Conductive Foam Core for Composite Processing
CN107084100A (en) * 2017-06-19 2017-08-22 东方电气风电有限公司 A kind of preparation method of wind electricity blade heating ice melting system based on graphene heating film and the blade
US20180002024A1 (en) * 2016-07-04 2018-01-04 Leonardo S.P.A. Structural element with heater for a vehicle, manufacturing method and operating method
JP2018031098A (en) * 2016-08-26 2018-03-01 日本グラファイトファイバー株式会社 Pitch-based carbon milled fiber, thermally conductive molded body, and method for producing pitch-based carbon milled fiber
US20180370637A1 (en) * 2017-06-22 2018-12-27 Goodrich Corporation Electrothermal ice protection systems with carbon additive loaded thermoplastic heating elements
CN109862637A (en) * 2019-01-18 2019-06-07 南京航空航天大学 A kind of anti-icing electric heating structure and preparation method using graphene-carbon nanotube composite material
CN110240783A (en) * 2019-06-24 2019-09-17 湖南东映碳材料科技有限公司 A kind of preparation method of low deformation big L/D ratio roller
CN110510145A (en) * 2019-08-30 2019-11-29 中国民用航空飞行学院 A three-beam composite wing integral structure and its forming process method
EP3593972A1 (en) * 2018-07-09 2020-01-15 Airbus Operations, S.L. Panel structure for an aircraft and manufacturing method thereof
CN211868686U (en) * 2020-03-23 2020-11-06 中国民用航空飞行学院 A curing system for glass fiber reinforced resin matrix composites

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012004942A1 (en) * 2012-03-12 2013-09-12 Munich Composites Gmbh Process for producing a preform and a fiber composite prefabricated component produced therefrom
KR20160083519A (en) * 2014-12-31 2016-07-12 주식회사 삼양사 Long-fiber reinforced thermoplastic resin composition with excellent thermal conductivity and mechanical properties
CN205022011U (en) * 2015-10-13 2016-02-10 山东柏远复合材料科技有限公司 Continuous densification of fiber reinforcement thermoset plastics pipeline, high -efficient production line
US20170238367A1 (en) * 2016-02-15 2017-08-17 General Electric Company Integrated Conductive Foam Core for Composite Processing
CN205439290U (en) * 2016-02-26 2016-08-10 深圳市梦之坊通信产品有限公司 Combined material cell phone case's exhausted formula molding device
US20180002024A1 (en) * 2016-07-04 2018-01-04 Leonardo S.P.A. Structural element with heater for a vehicle, manufacturing method and operating method
JP2018031098A (en) * 2016-08-26 2018-03-01 日本グラファイトファイバー株式会社 Pitch-based carbon milled fiber, thermally conductive molded body, and method for producing pitch-based carbon milled fiber
CN107084100A (en) * 2017-06-19 2017-08-22 东方电气风电有限公司 A kind of preparation method of wind electricity blade heating ice melting system based on graphene heating film and the blade
US20180370637A1 (en) * 2017-06-22 2018-12-27 Goodrich Corporation Electrothermal ice protection systems with carbon additive loaded thermoplastic heating elements
EP3593972A1 (en) * 2018-07-09 2020-01-15 Airbus Operations, S.L. Panel structure for an aircraft and manufacturing method thereof
CN109862637A (en) * 2019-01-18 2019-06-07 南京航空航天大学 A kind of anti-icing electric heating structure and preparation method using graphene-carbon nanotube composite material
CN110240783A (en) * 2019-06-24 2019-09-17 湖南东映碳材料科技有限公司 A kind of preparation method of low deformation big L/D ratio roller
CN110510145A (en) * 2019-08-30 2019-11-29 中国民用航空飞行学院 A three-beam composite wing integral structure and its forming process method
CN211868686U (en) * 2020-03-23 2020-11-06 中国民用航空飞行学院 A curing system for glass fiber reinforced resin matrix composites

Non-Patent Citations (5)

* Cited by examiner, † Cited by third party
Title
CHEN SHU-XIAN: "3D Unsteady Analysis of Temperature and Thermal Stress Fields of Resin Matrix Composite during Curing Process", 《JOURNAL OF UNIVERSITY OF ELECTRONIC SCIENCE AND TECHNOLOGY OF CHINA》, 30 July 2014 (2014-07-30), pages 547 - 51 *
MENG, FC: "An electromechanical behavior of reduced graphene oxide fiber", 《CARBON》, 15 June 2016 (2016-06-15), pages 244 - 247 *
刘国春: "基于涡流加热的环氧树脂/钴粉复合材料的除冰性能", 《合成树脂及塑料》, 25 November 2019 (2019-11-25), pages 23 - 26 *
戴海军: "纬编双轴向织物/环氧树脂电加热复合材料电热及层间剪切性能", 《复合材料学报》, 29 November 2019 (2019-11-29), pages 1997 - 2004 *
王程成;贺德龙;崔溢;: "结构-导电复合材料研究进展", 材料工程, no. 09, 11 September 2018 (2018-09-11) *

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