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High-heat-conducting carbon/carbon composite material and preparation method thereof

A carbon composite material and high thermal conductivity technology, applied in the field of carbon material manufacturing, can solve problems such as cumbersome process flow, achieve broad application prospects, less equipment, and low energy consumption

Active Publication Date: 2018-06-01
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the current hot press forming method to prepare carbon / carbon composite materials is mainly based on low temperature hot press forming, which can only realize the forming of composite materials, and further densification treatment, high temperature treatment and ultra-high temperature graphitization treatment are required in the follow-up process. Also more cumbersome

Method used

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preparation example Construction

[0023] An embodiment of the present invention provides a method for preparing a high thermal conductivity carbon / carbon composite material, comprising the following steps:

[0024] Step 1. Alternate laying of carbon fiber cloth with room temperature thermal conductivity greater than 500W / mK and mesophase pitch felt to obtain a laminated structure;

[0025] Step 2. Carrying out hot press molding, high temperature treatment and high pressure graphitization treatment on the laminated layer to obtain a carbon / carbon composite material with high thermal conductivity.

[0026] In the preparation method of the high thermal conductivity carbon / carbon composite material provided by the embodiment of the present invention, the laminated structure is obtained by alternately laminating the mesophase pitch in the form of a thin felt and the carbon fiber cloth reinforcement, which greatly reduces the carbon fiber laying process. The time for introducing mesophase pitch is simple and easy to...

Embodiment 1

[0039] 1) The ThermalGraph fabric EWC-600X eight pieces of satin (high thermal conductivity carbon fiber cloth) produced by Cytec Company of the United States is selected as the reinforcement. 8*8;

[0040] 2) Select naphthalene-based mesophase pitch with a softening point of about 285°C as the matrix carbon precursor, and use a high-temperature calender to prepare a thin mat of mesophase pitch. The temperature of the rollers of the calender is controlled at around 320°C, and the thickness of the thin mat is controlled at 0.5mm. After the calendering is completed, the thin felt is passed through water for rapid cooling;

[0041] 3) Cut out high thermal conductivity carbon fiber cloth and mesophase pitch thin mat for alternate laying, then put it into an ultra-high temperature hot press, and start to heat up after closing the mold. The hot pressing process is: rise from RT (room temperature) to 300°C within 1 hour , after 30 minutes of heat preservation, pressurize to 1MPa, an...

Embodiment 2

[0044] 1) Choose the XN90 carbon fiber woven plain cloth produced by Nippon Graphite Fiber Corporation (NGF) as the reinforcement, the fiber specification is 2K, the thermal conductivity at room temperature is 500W / m·K, and the warp and weft density is 2*2;

[0045] 2) Select naphthalene-based mesophase pitch with a softening point of about 285°C as the matrix carbon precursor, and use a high-temperature calender to prepare a thin mat of mesophase pitch. The temperature of the rollers of the calender is controlled at about 320°C, and the thickness of the thin mat is controlled at ~0.1mm After the calendering is completed, the thin felt is passed through water for rapid cooling;

[0046] 3) Cut out high thermal conductivity carbon fiber cloth and mesophase pitch thin mat for alternate laying, then put it into an ultra-high temperature hot press, and start to heat up after closing the mold. The hot pressing process is: rise from RT (room temperature) to 300°C within 1 hour , aft...

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Abstract

The invention relates to a high-heat-conducting carbon / carbon composite material and a preparation method thereof, and belongs to the technical field of carbon material manufacturing. The preparationmethod comprises the following steps: alternately laying a carbon fiber cloth and intermediate phase asphalt felt to obtain a laminated structure, wherein the thermal conductivity of the carbon fibercloth is greater than 500W / mK at room temperature; carrying out hot-pressing forming on the laminated structure, and carrying out high-temperature treatment and high-pressure graphitizing treatment toobtain the high-heat-conducting carbon / carbon composite material. The method has the advantages of simple process, little time consumption, low energy consumption and the like, and the preparation rate and efficiency of the high-heat-conducting carbon / carbon composite material can be greatly improved. The prepared high-heat-conducting carbon / carbon composite material has a uniform internal structure and excellent heat conduction and mechanical properties, and has wide application prospects in the aspects of heat control and heat management in the fields of aerospace, nuclear reactor, electronic industry and the like.

Description

technical field [0001] The invention relates to a high thermal conductivity carbon / carbon composite material and a rapid preparation method thereof, belonging to the technical field of carbon material manufacturing. Background technique [0002] With the rapid development of science and technology, heat dissipation and thermal management have become key technologies for the development of many fields. Many electronic components of aerospace vehicles need to work normally at an ambient temperature of 40-60°C. With the development of electronic technology, aircraft electronic equipment is becoming smaller, lighter, and more compact in structure. During operation, a large amount of The heat dissipation also puts forward higher and higher requirements for heat dissipation materials, which are an important part of thermal control. Large-area thin-plate structures of space vehicles such as satellites, missile nose cones, solid rocket motor nozzles and other parts with severe work...

Claims

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Application Information

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IPC IPC(8): C04B35/83
CPCC04B35/83
Inventor 冯志海樊桢余立琼李炜李兴超
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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