High thermal conductivity and high strength carbon-based composite material and preparation method thereof

A carbon-based composite material and carbon composite material technology, applied in the field of carbon material manufacturing, can solve the problems of weak interlayer bonding and insufficient bending resistance, and achieve the effect of improving bending resistance and light weight

Active Publication Date: 2018-04-17
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the problems existing in the prior art, the present invention proposes a high-thermal-conductivity high-strength carbon-based composite material and its preparation method, which solv

Method used

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Example Embodiment

[0032] The embodiment of the present invention also provides a method for preparing a high thermal conductivity and high strength carbon-based composite material, which includes the following steps:

[0033] Step 1. Use carbon fiber cloth as a reinforcement, and use a gas-phase or liquid-phase carbon precursor to densify the reinforcement to obtain a dense carbon / carbon composite process part;

[0034] Step 2. Graphitize the dense composite material process part to obtain a carbon / carbon composite material plate;

[0035] Step 3. Use a silicon adhesive to bond at least two layers of the carbon / carbon composite material plates to obtain a high thermal conductivity and high strength carbon-based composite material.

[0036] The room temperature thermal conductivity of the carbon fiber described in step 1 is greater than 600W / m·K; the method for densifying the reinforcement in step 1 includes: chemical vapor deposition, chemical vapor infiltration, and liquid precursor One or any combina...

Example Embodiment

[0041] Example 1

[0042] 1) P120 high thermal conductivity carbon fiber with a specification of 2K is selected as the reinforcement, and the P120 high thermal conductivity carbon fiber is woven into eight satin carbon cloth with a warp and weft density of 8*8, the thickness of the carbon cloth is about 0.8mm;

[0043] 2). Cut the eight satin carbon cloth woven in step 1) into the target material size for use;

[0044] 3) Using propane and argon as gas sources, the eight satin carbon cloths cut in step 2) are densified by chemical vapor infiltration (CVI), the temperature is 950℃, and the treatment time is 200h;

[0045] 4) Put the sample of the densification process obtained in step 3) into a high-temperature graphitization furnace, fill it with argon gas, raise the temperature to 2500°C and keep it for 1 hour, and then cool it with the furnace;

[0046] 5) After repeating step 3) and step 4) twice, the process sample density reaches 1.85g / cm 3 ;

[0047] 6) Put the densification proces...

Example Embodiment

[0054] Example 2

[0055] 1) K13C high thermal conductivity carbon fiber with 2K specification is selected as the reinforcement, and the K13C high thermal conductivity carbon fiber is woven into eight satin carbon cloth with a warp and weft density of 8*8, and the thickness of the carbon cloth is about 0.8mm;

[0056] 2). Cut the eight satin carbon cloth woven in step 1 to the target material size and set aside;

[0057] 3). After fixing the single-layer carbon cloth cut in step 2 with a graphite perforated plate, it is put into a pitch impregnation tank, and the carbon cloth is impregnated with medium temperature coal pitch. The impregnation temperature is 240°C and the impregnation pressure is 3MPa. After the pressure is maintained for 1 hour, the temperature can be cooled freely while maintaining the pressure.

[0058] 4) Put the sample of the densification process after impregnating the pitch into a carbonization furnace for atmospheric carbonization. The carbonization process cur...

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Abstract

The invention provides a high thermal conductivity and high strength carbon-based composite material and a preparation method thereof and belongs to the technical field of manufacturing of carbon materials. The high thermal conductivity and high strength carbon-based composite material comprises at least two layers of carbon/carbon composite material plates which are laminated, and two adjacent layers of the carbon/carbon composite material plates are adhered by a silicon adhesive. As for the high thermal conductivity and high strength carbon-based composite material provided by the invention,the thermal conductivity is more than 450W/mK, the tensile strength and the compressive strength are more than 250MPa respectively, and the bending strength is more than 200MPa. Compared with an aluminum alloy material which is currently used for a heat dissipation panel of a spacecraft thermal control system, the mechanical performances of the material are comparable, but the mass is lighter andthe thermal conductivity is much higher than that of the aluminum alloy. Thus, the high thermal conductivity and high strength carbon-based composite material is expected to be widely applied in thefields of spacecraft thermal control, thermal management of electronic devices and the like.

Description

technical field [0001] The invention relates to a method for preparing a carbon-based composite material with high thermal conductivity and high strength, and belongs 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 in the development of deep space exploration in aerospace technology. Many electronic components of space 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. The heat dissipation material is an important material used in the thermal control system of the space vehicle. ...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B35/622B32B7/12B32B9/00B32B9/04B32B33/00
CPCB32B7/12B32B9/007B32B9/04B32B33/00B32B2307/302B32B2307/546B32B2307/558B32B2307/718C04B35/622C04B35/83C04B2235/5248C04B2235/614C04B2235/616
Inventor 冯志海樊桢余立琼李兴超李炜
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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