Carbon fiber aramid honeycomb composite board, preparation process and application thereof

Abstract

The application belongs to the technical field of energy-absorbing composite materials, and provides a carbon fiber aramid honeycomb composite plate and a preparation process thereof.The carbon fiber aramid honeycomb composite plate is composed of at least one aramid honeycomb core material containing polymer microspheres, carbon fiber plates located above and below the aramid honeycomb core material, and a glass fiber cloth located between the two carbon fiber plates.The number of layers of the carbon fiber plate is twice the number of layers of the aramid honeycomb core material, and the number of layers of the glass fiber cloth is one less than the number of layers of the aramid honeycomb.The composite plate has mechanical properties and energy-absorbing properties, is lightweight and high-strength, and has low cost.The carbon fiber aramid honeycomb composite plate can be prepared according to the scene requirements, and has a wide range of applications in the fields of aerospace, rail transportation, and other strong earthquake or strong impact scenes, and intelligent floor sensors.

Description

Technical Field

[0001] This invention belongs to the field of energy-absorbing composite material technology, and relates to a carbon fiber aramid honeycomb composite plate, its preparation process, and its application. Background Technology

[0002] Aramid materials are characterized by low density and low mass, while also possessing excellent impact resistance. However, with the continuous development of modern society, people have increasingly higher demands for the impact resistance of materials. The impact resistance of existing aramid materials can no longer meet these demands, and aramid materials themselves are also expensive. This limits the application of aramid materials in various fields.

[0003] Chinese invention patent application CN110341265A discloses an energy-absorbing composite material. The upper and lower surfaces of the composite material are made of aramid fiber cloth, the interlayer is made of glass fiber cloth, and the matrix is ​​aromatic resin. Glass fiber is used to replace part of the aramid fiber, and the aramid fiber cloth and glass fiber cloth are mixed to give full play to their respective excellent properties, thereby improving the elastic modulus of the material and effectively improving the impact resistance of the aramid composite material.

[0004] Chinese invention patent CN113276523B discloses a PBO fiber / aramid fiber reinforced composite material and its preparation method. The face plate of the composite material is a PBO fiber reinforced thermosetting resin composite material, and the back plate is an aramid fiber reinforced thermoplastic resin composite material. The thermosetting resin is a polyimide thermosetting resin, and the thermoplastic resin is a polyimide thermoplastic resin. A high-strength aramid composite material is prepared by bonding PBO fibers and aramid fibers.

[0005] The above technologies all employ methods of mixing or compounding with other materials to improve the strength and lifespan of aramid materials. However, this still relies on the material's inherent properties to absorb energy from external impacts, which can easily lead to material fatigue or damage, resulting in a decline in various aspects of the material's performance. Carbon fiber aramid honeycomb sandwich composite material consists of a thick, lightweight aramid paper honeycomb core sandwiched between two carbon fiber composite panels, bonded together with adhesives under specific temperature and pressure conditions to form a rigid, integral structure. The lightweight honeycomb core material possesses a high strength-to-weight ratio and fatigue resistance, while the fiber layers provide reinforcement.

[0006] Chinese invention patent CN105291524B discloses an aramid honeycomb sandwich panel and its processing method. The aramid honeycomb sandwich panel includes at least one aramid honeycomb core and a reinforcing layer, wherein the reinforcing layer has one more layer than the aramid honeycomb core. At least one sidewall of the aramid honeycomb sandwich panel has an irregularly shaped surface. An aramid honeycomb core is sandwiched between every two adjacent reinforcing layers to meet the requirements of aramid honeycomb materials with special shapes. However, it mainly focuses on the design of curved structures and lacks optimization of the material's mechanical properties, wave absorption properties, and fatigue resistance.

[0007] To expand the application of aramid materials in aerospace, rail transportation, and sensors, and to prepare aramid honeycomb materials suitable for more scenarios, it is necessary and urgent to improve the current aramid honeycomb materials. While ensuring low cost and simple preparation process, it is also necessary to comprehensively consider the improvement of its mechanical properties, wave absorption properties, and fatigue resistance. Summary of the Invention

[0008] This invention addresses the problems of low strength, poor wave absorption performance, and short lifespan of existing energy-absorbing composite materials by providing a carbon fiber aramid honeycomb composite panel, its preparation process, and its application. This composite panel is lightweight and high-strength, possessing both high wave absorption performance and fatigue resistance; it is also low in cost and simple to prepare; it has excellent overall performance and wider applications.

[0009] The technical solution of the present invention is as follows:

[0010] A carbon fiber aramid honeycomb composite panel comprises at least one layer of aramid honeycomb core material containing polymer microspheres, carbon fiber plates located above and below the aramid honeycomb core material, and glass fiber cloth located between the two carbon fiber plates; the number of carbon fiber plates is twice the number of layers of the aramid honeycomb core material, and the number of layers of the glass fiber cloth is the same as that of the aramid honeycomb.

[0011] In this invention, aramid material has the characteristics of low density and low mass and excellent impact resistance. At the same time, by utilizing the good mechanical properties of its honeycomb structure and adding polymer microspheres that can be used for power generation into the aramid honeycomb core, the impact resistance of aramid material and the collection and conversion of vibration energy are achieved.

[0012] Furthermore, the aramid honeycomb core material has regular hexagonal or concave hexagonal cells with a cell side length of 1.5-4 mm; the density of the aramid honeycomb core material is 25-48 kg / m³. 3 .

[0013] Furthermore, the aramid honeycomb core material has 1-5 layers, and the thickness of a single layer is 2-3 mm.

[0014] In this invention, the number of layers and thickness of the finished carbon fiber aramid honeycomb composite panel can be adjusted according to actual needs. Considering energy collection efficiency, the preferred number of layers is 1-5.

[0015] Furthermore, the polymer microspheres are selected from at least one of polytetrafluoroethylene microspheres, polyvinyl chloride microspheres, and polyoxymethylene microspheres.

[0016] Furthermore, the diameter of the polymer microspheres is 1 mm or less smaller than the maximum diameter of polymer microspheres that can be placed within the honeycomb pores.

[0017] In some embodiments of the present invention, when the maximum polymer microsphere that can be placed in the honeycomb cell is x (mm), the actual diameter of the polymer microsphere used is x-1 to x (mm); in this way, the optimal energy absorption efficiency and mechanical properties are obtained while ensuring that the polymer microsphere can move freely in the honeycomb cell; if the diameter of the polymer microsphere is less than x-1 (mm), the energy absorption efficiency and mechanical properties of the carbon fiber aramid honeycomb composite board will decrease significantly.

[0018] This invention also provides a method for preparing the above-mentioned carbon fiber aramid honeycomb composite material plate, specifically including the following steps:

[0019] (1) Preparation of aramid honeycomb core material and carbon fiber plate;

[0020] (2) Place polymer microspheres in the gaps of aramid honeycomb core material and attach the heat-breaking adhesive film to the upper and lower end faces to obtain aramid honeycomb core material containing polymer microspheres.

[0021] (3) Assemble the carbon fiber plate, aramid honeycomb core material containing polymer microspheres, carbon fiber plate and glass fiber cloth in that order, and then preheat, heat, blow air and cool to obtain the product.

[0022] In some embodiments of the present invention, the heat-breaking adhesive film comprises, by weight, 65-85 parts resin, 5-15 parts adhesive film, and 5-10 parts accelerator; the resin is selected from one or more of epoxy resin, polyvinyl alcohol, polyethylene, polypropylene, and bismaleimide resin.

[0023] Furthermore, the method for preparing the aramid honeycomb core material is as follows:

[0024] A1: Apply adhesive to aramid paper, stack them in a staggered manner, and obtain honeycomb laminated strips after curing;

[0025] A2: Stretch the honeycomb laminate strips to form honeycomb cells;

[0026] A3: After forming a honeycomb structure, the aramid honeycomb core material is obtained through impregnation, curing, and cooling.

[0027] Furthermore, in step A3, the impregnation process uses a polyimide aqueous solution with a solid content of 15-50%, and the impregnation time is 15-30 min; the curing and molding conditions are: heating from room temperature to 350-400℃ at a rate of 2-5℃ / min, holding the temperature for 2-3 hours, and then cooling down to below 60℃.

[0028] In some embodiments of the present invention, step A3 is repeated 1-8 times.

[0029] In some embodiments of the present invention, the specific operation of coating adhesive on aramid paper is as follows: the adhesive is applied onto the aramid paper using a coating roller with a groove width four times the side length of the honeycomb grid.

[0030] In some embodiments of the present invention, step A2 uses a stretching rate of 20-300 mm / s.

[0031] Furthermore, the method for preparing the carbon fiber plate is as follows:

[0032] B1: Mix carbon nanotubes and adhesive resin and stir until homogeneous to obtain a carbon-resin mixture;

[0033] B2: Add curing agent to carbon-resin mixture, stir and mix evenly to obtain carbon fiber bonding resin;

[0034] B3: Carbon fiber bonding resin is coated onto carbon fiber cloth through impregnation, and after cooling, carbon fiber sheet is obtained.

[0035] Furthermore, the mass ratio of the carbon nanotubes, adhesive resin, and curing agent is 0.3-5:40-60:10-30.

[0036] Furthermore, the adhesive resin is selected from any one of epoxy resin, phenolic resin, and polyamino resin.

[0037] Furthermore, the carbon fiber bonding resin coating thickness is 100-400 nm.

[0038] Furthermore, the impregnation temperature is room temperature to 80°C, and the impregnation time is 20 to 100 minutes.

[0039] In some embodiments of the present invention, the carbon fiber cloth is of type 15k or 24k, and the glass fiber cloth is of type EWR200-100 or EWR300-100.

[0040] Furthermore, in step (3), the preheating temperature is 100-150℃ and the preheating time is 2-5 min.

[0041] Furthermore, in step (3), the heating time is 30-60 seconds.

[0042] Furthermore, in step (3), the blowing speed is 0.2-0.5 m / s.

[0043] Furthermore, in step (3), the cooling time is 15-90 min.

[0044] The present invention also provides the application of any of the above-described carbon fiber aramid honeycomb composite panels or carbon fiber aramid honeycomb composite panels prepared by any of the above-described preparation processes in aerospace materials, rail transit materials or sensor materials.

[0045] Compared with the prior art, the present invention has the following beneficial effects:

[0046] (1) The present invention utilizes the aramid honeycomb structure to provide the carbon fiber aramid honeycomb composite plate with good mechanical properties, energy absorption properties and fatigue resistance;

[0047] (2) This invention improves the single-layer energy absorption efficiency by optimizing the number of layers in the carbon fiber aramid honeycomb composite plate;

[0048] (3) Adding polymer microspheres that can be used for power generation into the aramid honeycomb voids has improved the strength of aramid materials and enabled the collection and conversion of vibration energy; it has solved the problems of insufficient strength and high cost of traditional aramid materials, and at the same time, it has collected the energy generated by the impact, realizing the recycling of energy.

[0049] (4) The present invention can prepare corresponding carbon fiber aramid honeycomb composite material plates according to the needs of the scenario. It has important applications in aerospace, rail transportation and other strong earthquake or strong impact scenarios. It can also be used in the field of sensors such as smart floors. Attached Figure Description

[0050] Figure 1 This is a process flow diagram for the preparation of the carbon fiber aramid honeycomb composite plate of the present invention;

[0051] Figure 2 This is a schematic diagram of the carbon fiber aramid honeycomb composite panel structure in Embodiment 1 of the present invention;

[0052] Figure 3 These are cross-sectional views of the honeycomb structure of the core layer of the carbon fiber aramid honeycomb composite board in Examples 1(a) and 2(b) of the present invention;

[0053] Figure 4 This is a graph showing the energy absorption performance of the carbon fiber aramid honeycomb composite panel in Embodiment 1 of the present invention.

[0054] Figure 5 This is a fatigue force-displacement curve of the carbon fiber aramid honeycomb composite plate in Embodiment 1 of the present invention.

[0055] Reference numerals: 1. Aramid paper; 2. Coating roller; 3. Stretching channel; 4. Stretching machine; 5. Glue tank; 6. Blower oven; 7. Coating machine; 8. Thermal breakage equipment working chamber. Detailed Implementation

[0056] The following non-limiting embodiments are intended to enable those skilled in the art to gain a more comprehensive understanding of the present invention, but do not limit the invention in any way. The following content is merely an exemplary description of the scope of protection of the present invention, and those skilled in the art can make various changes and modifications to the invention based on the disclosed content, which should also fall within the scope of protection of the present invention.

[0057] The following examples are combined Figure 1 The flowchart shown illustrates the preparation process of the carbon fiber aramid honeycomb composite board of the present invention.

[0058] Example 1

[0059] I. Preparation of Aramid Honeycomb Core Material:

[0060] (1) Apply the core strip adhesive to the aramid paper 1 using a coating roller 2 with a groove width four times the side length of the honeycomb grid. After the coated aramid paper is stacked in an offset manner and naturally cured, a honeycomb laminated strip is obtained.

[0061] (2) Assemble the honeycomb laminated strip on the stretching channel 3 of the stretching machine 4 and stretch it at a rate of 50 mm / s until the honeycomb laminated strip forms a regular hexagonal honeycomb structure (the side length of the regular hexagonal honeycomb in this embodiment is 1.5 mm).

[0062] (3) Place it in a glue tank 5 containing a polyimide aqueous solution with a solid content of 20wt%, immerse it in the glue for 15-30 minutes, and then cure it in a forced-air oven 6. The temperature is increased from room temperature to 350℃ at a heating rate of 5℃ / min, then kept at a constant temperature for 2 hours, and then cooled down to no more than 60℃ before taking it out.

[0063] (4) Repeat this step twice to prepare aramid honeycomb core material.

[0064] II. Preparation of carbon fiber sheets:

[0065] (1) Take 1 part by weight of carbon nanotubes and 60 parts by weight of adhesive resin (epoxy resin is selected), mix them, and stir evenly to obtain carbon-resin mixture.

[0066] (2) Add 10 parts by weight of curing agent (polyamide) to the carbon-resin mixture, stir and mix for 2 hours until it is uniformly mixed to obtain a highly conductive carbon fiber bonding resin.

[0067] (3) Connect the wires to the pre-cut carbon fiber cloth, and then use the coating machine 7 to coat the carbon fiber cloth with the wires connected with high conductivity carbon fiber adhesive resin. The coating thickness is 100-400μm. The heating temperature during coating does not exceed 80℃ and the heating time is 20-100min. After coating, place it at room temperature to cool for more than 2 hours to prepare a high conductivity carbon fiber board.

[0068] III. Preparation of polymer microsphere-aramid honeycomb core structure panel:

[0069] Polymer microspheres (polytetrafluoroethylene microspheres) with a diameter of 2 mm are placed in the gaps of aramid honeycomb core material, and then a heat-breaking adhesive film is smoothly attached to its end face to obtain a polymer microsphere-aramid honeycomb core material structure board.

[0070] IV. Preparation of carbon fiber aramid honeycomb composite panels:

[0071] (1) Assemble the carbon fiber plate, polymer microsphere-aramid honeycomb core material structure plate, carbon fiber plate, and glass fiber cloth in that order.

[0072] (2) It is placed in the working chamber 8 of the hot breaking equipment for hot breaking treatment. After it cools and solidifies, carbon fiber aramid honeycomb composite board is prepared.

[0073] (3) Three carbon fiber aramid honeycomb composite material plates are stacked and bonded together to obtain a three-layer carbon fiber aramid honeycomb composite plate (its structure is as follows). Figure 1 (As shown).

[0074] Example 2

[0075] I. Preparation of Aramid Honeycomb Core Material:

[0076] (1) Apply the core strip adhesive to the aramid paper 1 using a coating roller 2 with a groove width four times the side length of the honeycomb grid. After the coated aramid paper is stacked in an offset manner and naturally cured, a honeycomb laminated strip is obtained.

[0077] (2) Assemble the honeycomb laminate strip on the stretching channel 3 of the stretching machine 4 and stretch it at a rate of 300 mm / s until the honeycomb laminate strip forms a concave hexagonal honeycomb structure (in this embodiment, the side length of the concave hexagonal honeycomb is 5 mm).

[0078] (3) Place it in a glue tank 5 containing a polyimide aqueous solution with a solid content of 20wt%, immerse it in the glue for 15-30 minutes, and then cure it in a forced-air oven 6. The temperature is increased from room temperature to 400℃ at a heating rate of 5℃ / min, then kept at a constant temperature for 3 hours, and then cooled down to no more than 60℃ before taking it out.

[0079] (4) Repeat this step 8 times to prepare aramid honeycomb core material.

[0080] II. Preparation of carbon fiber sheets:

[0081] (1) Take 5 parts by weight of carbon nanotubes and 40 parts by weight of adhesive resin (phenolic resin is selected), mix them, and stir evenly to obtain carbon-resin mixture.

[0082] (2) Add 30 parts by weight of curing agent (polyamide) to the carbon-resin mixture, stir and mix for 5 hours until it is uniformly mixed to obtain a highly conductive carbon fiber bonding resin.

[0083] (3) Connect the wires to the pre-cut carbon fiber cloth, and then use an impregnation machine to coat the carbon fiber cloth with the wires connected with high conductivity carbon fiber adhesive resin. The coating thickness is 100-400μm. The heating temperature during coating does not exceed 80℃ and the heating time is 20-100min. After coating, place it at room temperature to cool for more than 2 hours to prepare a high conductivity carbon fiber board.

[0084] III. Preparation of polymer microsphere-aramid honeycomb core structure panel:

[0085] Polymer microspheres (using polytetrafluoroethylene microspheres) with a diameter of 2 mm are placed in the gaps of aramid honeycomb core material, and then a heat-breaking adhesive film is smoothly applied to its end face to obtain a polymer microsphere-aramid honeycomb core material structure board.

[0086] IV. Preparation of carbon fiber aramid honeycomb composite panels:

[0087] (1) Assemble the carbon fiber plate, polymer microsphere-aramid honeycomb core material structure plate, carbon fiber plate, and glass fiber cloth in that order.

[0088] (2) It is placed in the working chamber 8 of the hot breaking equipment for hot breaking treatment. After it cools and solidifies, carbon fiber aramid honeycomb composite board is prepared.

[0089] (3) Three carbon fiber aramid honeycomb composite material plates are stacked and bonded together to obtain a three-layer carbon fiber aramid honeycomb composite plate.

[0090] Comparative Example 1

[0091] The difference from Example 1 is that step four-(3) is as follows:

[0092] Seven carbon fiber aramid honeycomb composite panels are stacked and bonded together to obtain a seven-layer carbon fiber aramid honeycomb composite panel.

[0093] The other steps are the same as in Example 1.

[0094] Comparative Example 2

[0095] The difference from Example 1 is that steps one - (1) and (2) are as follows:

[0096] (1) Apply the core strip adhesive to the aramid paper using a coating roller with a groove width four times the side length of the honeycomb grid. After the coated aramid paper is stacked in an offset manner and cured naturally, a triangular laminated strip is obtained.

[0097] (2) Assemble the triangular laminated strip on the stretching machine and stretch it at a rate of 20-300 mm / s until the honeycomb laminated strip forms a triangular honeycomb structure (side length is 4 mm).

[0098] The other steps are the same as in Example 1.

[0099] Comparative Example 3

[0100] The difference from Example 1 is that step three is omitted, that is, the pores of the aramid honeycomb core material do not contain polymer microspheres.

[0101] Comparative Example 4

[0102] The difference from Example 1 is that the honeycomb laminate strips form a regular hexagonal honeycomb structure with a side length of 2 mm.

[0103] Test case

[0104] (1) Energy absorption efficiency test: Each sample plate was cut into 500mm×500mm pieces, stacked in multiple layers, glued together, and fixed to the surface of the vibrator. The vibrator was adjusted to a frequency of 60Hz and a vibration amplitude of 1.5mm to simulate the energy absorption of the sample plate when resisting impact. The sample plate was then connected to an electrical instrument to measure and calculate its total energy absorption efficiency and the energy absorption efficiency of each layer.

[0105] (2) Mechanical performance test: Each sample plate is cut into 500mm×500mm, multi-layered and glued together and fixed on a pendulum tester to simulate the impact condition of the sample plate. The sample plate is then connected to an electrical instrument to determine its maximum impact strength.

[0106] The microwave absorption performance test of the carbon fiber aramid honeycomb composite panel in Example 1 above is shown in [reference needed]. Figure 1 The performance test results of the carbon fiber aramid honeycomb composite panels prepared in Examples 1-2 and Comparative Examples 1-4 are shown in Tables 1-2.

[0107] Table 1 Energy absorption efficiency results

[0108]

[0109]

[0110] Table 2 Mechanical property test results

[0111] serial number Impact resistance Example 1 <![CDATA[92.1kJ / m 2 ]]> Example 2 <![CDATA[101.6kJ / m 2 ]]> Comparative Example 1 <![CDATA[155.2kJ / m 2 ]]> Comparative Example 2 <![CDATA[67.9kJ / m 2 ]]> Comparative Example 3 <![CDATA[92.3kJ / m 2 ]]> Comparative Example 4 <![CDATA[84.5kJ / m 2 ]]>

[0112] The results above show that while excessive layers in carbon fiber aramid honeycomb composite panels improve impact resistance and fatigue resistance, they significantly reduce single-layer energy absorption efficiency, making them unfavorable for energy harvesting. Furthermore, the shape of the aramid honeycomb cells significantly impacts the performance of the composite panel, particularly its impact resistance. Compared to regular hexagons or concave hexagons, triangular structures are less effective at improving impact resistance, and also decrease single-layer energy absorption efficiency and fatigue resistance. Additionally, when the honeycomb side length and sphere diameter are too small, while mechanical properties improve slightly, power generation performance declines significantly. Conversely, when the honeycomb side length is too large, while energy conversion capacity increases, impact resistance and fatigue resistance are compromised. Furthermore, according to... Figure 4 and Figure 5 It can be concluded that the presence of the aramid honeycomb core layer and its polymer microspheres not only does not affect the mechanical properties of the original carbon fiber plate, but also gives the carbon fiber plate good energy collection performance.

[0113] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, and is not intended to limit the scope of protection of the present invention. Simple modifications or equivalent substitutions made by those skilled in the art to the technical solution of the present invention do not depart from the essence and scope of the technical solution of the present invention.

Claims

1. A carbon fiber aramid honeycomb composite panel, characterized in that, The carbon fiber aramid honeycomb composite panel consists of at least one layer of aramid honeycomb core material containing polymer microspheres, carbon fiber plates located above and below the aramid honeycomb core material, and glass fiber cloth located between the two carbon fiber plates; the number of carbon fiber plates is twice the number of aramid honeycomb core material layers, and the number of glass fiber cloth layers is one less than the number of aramid honeycomb layers; the number of aramid honeycomb core material layers is 1-5. The aramid honeycomb core material has regular hexagonal or concave hexagonal honeycomb cells; the side length of the honeycomb cells is 1.5-4 mm. The polymer microspheres are selected from at least one of polytetrafluoroethylene microspheres, polyvinyl chloride microspheres, and polyoxymethylene microspheres; the diameter of the polymer microspheres is 1 mm or less smaller than the diameter of the largest polymer microsphere that can be placed in the honeycomb pores.

2. The carbon fiber aramid honeycomb composite panel according to claim 1, characterized in that, The density of aramid honeycomb core material is 25-48 kg / m³. 3 .

3. The preparation process of the carbon fiber aramid honeycomb composite panel according to claim 1 or 2, characterized in that, Includes the following steps: (1) Preparation of aramid honeycomb core material and carbon fiber plate; (2) Place polymer microspheres in the pores of aramid honeycomb core material and attach the heat-breaking adhesive film to the upper and lower end faces to obtain aramid honeycomb core material containing polymer microspheres; (3) Assemble the carbon fiber plate, aramid honeycomb core material containing polymer microspheres, carbon fiber plate and glass fiber cloth in that order, and then preheat, heat, blow air and cool to obtain the product.

4. The preparation process according to claim 3, characterized in that, The method for preparing the aramid honeycomb core material is as follows: A1: Apply adhesive to aramid paper, stack them in a staggered manner, and obtain honeycomb laminated strips after curing; A2: Stretch the honeycomb laminate strips to form honeycomb cells; A3: After forming a honeycomb structure, the aramid honeycomb core material is obtained through impregnation, curing, and cooling.

5. The preparation process according to claim 4, characterized in that, In step A3, the impregnation process uses a polyimide aqueous solution with a solid content of 15-50wt% and the impregnation time is 15-30min; the curing and molding conditions are: heating from room temperature to 350-400℃ at a rate of 2-5℃ / min, holding the temperature for 2-3h, and then cooling down to below 60℃.

6. The preparation process according to claim 3, characterized in that, The carbon fiber plate is prepared as follows: B1: Mix carbon nanotubes and adhesive resin and stir until homogeneous to obtain a carbon-resin mixture; B2: Add curing agent to carbon-resin mixture, stir and mix evenly to obtain carbon fiber bonding resin; B3: Carbon fiber bonding resin is coated onto carbon fiber cloth through impregnation, and after cooling, carbon fiber sheet is obtained.

7. The preparation process according to claim 6, characterized in that, The mass ratio of the carbon nanotubes, adhesive resin, and curing agent is 0.3-5:40-60:10-30; the adhesive resin is selected from any one of epoxy resin, phenolic resin, and polyamino resin. The thickness of the carbon fiber bonding resin coating is 100-400 nm; The immersion temperature is room temperature to 80°C, and the immersion time is 20 to 100 minutes.

8. The preparation process according to claim 3, characterized in that, In step (3), the preheating temperature is 100-150℃, the preheating time is 2-5 min, the heating time is 30-60 s, the blowing speed is 0.2-0.5 m / s, and the cooling time is 15-90 min.

9. The application of the carbon fiber aramid honeycomb composite plate according to claim 1 or 2 or the carbon fiber aramid honeycomb composite plate prepared by any of the preparation processes according to claims 3-8 in aerospace materials, rail transit materials or sensor materials.

Images