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Preparation method of carbon-carbon composite material with high thermal conductivity

A technology of carbon-carbon composite materials and high thermal conductivity, which is applied in the direction of heat exchange materials, chemical instruments and methods, etc., can solve the problems of high energy consumption and low thermal conductivity of composite materials, and achieve high mechanical properties, controllable molecular weight, Effects from a wide range of sources

Active Publication Date: 2013-10-30
SHANXI INST OF COAL CHEM CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The material setting needs to be completed within the temperature range of 500-800°C, which consumes a lot of energy, and the thermal conductivity of the prepared composite material is not high

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0018] The diameter is 10-12 microns, the monofilament density is 1.86g / cm 3 The mesophase carbon fibers are arranged in parallel to form a thin carbon fiber layer with a thickness of 2-3 mm and placed in a flat plate, and a layer of COPNA resin powder is evenly spread on it (the weight ratio of fiber to resin is 0.8: 1), and the temperature Increase the temperature to 110±2°C and keep it for 1 hour to allow the resin powder to fully melt and coat a layer of resin film on the surface of the carbon fiber. After natural cooling, it is cut into square slices of 30×50mm. These sheets are then stacked one after the other in a square mold. Pressurize to 20±1MPa. At the same time, raise the temperature of the mold to within the range of 115±1°C, release the pressure and keep it for 1 hour, then raise the temperature to 210±5°C for curing, and the curing time is controlled at 2.5 hours. After curing, it was naturally cooled to room temperature and released from the mold. The sample...

Embodiment 2

[0020] The diameter is 13-15 microns, the monofilament density is 1.85g / cm 3 The mesophase carbon fibers are arranged in parallel to form a thin layer of carbon fibers with a thickness of 2-3 mm and placed in a flat plate, and a layer of COPNA resin powder is evenly spread on it (the weight ratio of fiber to resin is 1.5: 1), and the temperature Raise to 130±2°C and keep for 0.8 hours to allow the resin powder to fully melt and coat a layer of resin film on the surface of the carbon fiber. After natural cooling, it is cut into square slices of 30×50mm. These sheets are then stacked one after the other in a square mold. Pressurize to 30±1MPa. At the same time, raise the temperature of the mold to within the range of 125±2°C, keep the pressure off for 1.5 hours, then raise the temperature to 250±5°C for curing, and control the curing time to 4 hours. After curing, the demoulding samples were naturally cooled to room temperature and then subjected to a carbonization-mesophase ...

Embodiment 3

[0022] The diameter is 15-17 microns, the monofilament density is 1.83g / cm 3 The carbon fibers of the mesophase are arranged in parallel to form a thin layer of carbon fibers with a thickness of 2-3 mm in a flat plate, and a layer of COPNA resin powder is evenly spread on it (the weight ratio of fiber to resin is 2: 1), - Sprinkle a layer of COPNA resin powder evenly on the carbon fiber with a thickness of 3 mm (the weight ratio of fiber to resin is 2), raise the temperature to 135±2°C for 1 hour, let the resin powder fully melt on the carbon The fiber surface is coated with a layer of resin film. After natural cooling, it is cut into square slices of 30×50mm. These sheets are then stacked one after the other in a square mold. Pressurize to 50±1MPa. At the same time, the temperature of the mold is raised to 140±2°C, and the pressure is released for 2 hours, and then the temperature is raised to 280±5°C for curing, and the curing time is controlled at 2 hours. After curing,...

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Abstract

A preparation method of a carbon-carbon composite material with high thermal conductivity comprises the following steps: parallelly arranging mesophase asphalt-based carbon fibers in a flat plate, uniformly spreading a layer of condensed polynuclear aromatic hydrocarbon resin powder on the mesophase asphalt-based carbon fibers, heating the resin powder for fully melting so as to coat a resin film layer on the fiber surface, naturally cooling to obtain a carbon fiber preform; or dissolving the condensed polynuclear aromatic hydrocarbon resin by an organic solvent to prepare a solution, soaking the mesophase asphalt-based carbon fibers in the solution, completely volatilizing the solvent to form a resin layer on the fiber surface so as to obtain the carbon fiber preform; cutting the carbon fiber preform into thin sheets according to a desired dimension, orderly stacking the sheet-like carbon fiber preform in a mold, performing pressurization to 20-70 MPa, heating to 110-145 DEG C, performing depressurization, maintaining for 0.5-2 hours, heating again to 200-300 DEG C, curing for 1-6 hours, after curing, naturally cooling to room temperature for demolding, performing carbonization at 900 DEG C of the obtained cured sample, soaking the sample with asphalt at a soaking temperature of 340-400 DEG C for soaking time of 1-8 hours, repeating the carbonization-soaking cyclic process to increase the sample density to 1.5-1.7 g / cm3, and performing graphitization to prepare the carbon-carbon composite material with high thermal conductivity. The invention has the advantages of low energy consumption and high thermal conductivity.

Description

technical field [0001] The invention belongs to a preparation method of a carbon-carbon composite material, and in particular relates to a preparation technology of a high thermal conductivity carbon-carbon composite material. Background technique [0002] In the field of aerospace, such as aircraft, missiles and recoverable satellites, high-speed flight and airflow friction will generate extremely high temperatures in a short period of time when re-entering the atmosphere. Therefore, it is necessary to have a high thermal conductivity between the surface and the interior of the satellite or missile to conduct the heat flow out in time to ensure the normal operation of the internal instruments. Traditional materials use metals with high thermal conductivity, such as copper, or titanium alloys. However, the proportion of these metal materials is too large, which is not conducive to the long-range flight of the missile. This requires the development of new composite material...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C09K5/14
Inventor 史景利张金才郭全贵刘朗
Owner SHANXI INST OF COAL CHEM CHINESE ACAD OF SCI
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