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C/C-MC composite of mixed matrix thermal structure and preparation method thereof

A composite material, C-MC technology, applied in the field of carbon/carbon composite material manufacturing, can solve the problems of unavoidable application of oxidation protection near space vehicles, loss of overall load-bearing performance, etc., and achieve the integration of load-bearing and heat-proof functions , Improving the anti-oxidation performance and strengthening the load-bearing performance

Active Publication Date: 2016-10-12
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

Single direction and single outstanding performance will make the anisotropy of the material more obvious, and can only maintain the bearing capacity in one direction, but lose the overall bearing capacity under complex loads
In addition, since carbon / carbon composite materials begin to oxidize above 400°C, solving the problem of oxidation protection of materials is an unavoidable problem in the application of near space vehicles

Method used

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Examples

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preparation example Construction

[0035] A preparation method of a hybrid matrix thermal structure C / C-MC composite material, the steps are:

[0036] 1) Select domestic T300-1K, T300-3K polyacrylonitrile (PAN)-based carbon fibers to weave into carbon cloth (satin, plain or twill), and cut into 300mm× according to 0°, +45°, 90°, -45° 300mm carbon cloth block is spare; take the warp as 0°, rotate 45° counterclockwise to form +45°, rotate 90° counterclockwise to form 90°, and rotate 135° counterclockwise to form -45°;

[0037] 2) Laminate the carbon cloth blocks in step 1) according to the design parameters, stack them to a certain thickness and stitch them at a certain interval along the thickness direction to form a three-dimensional fabric;

[0038] 3) The three-dimensional fabric stitched in step 2) is heat-treated at a certain temperature to form a carbon fiber preform;

[0039] 4) The carbon fiber preform obtained in step 3) is subjected to chemical vapor deposition as required, and the carbon fiber interface treat...

Embodiment 1

[0052] 1) Select general-purpose T300-1K PAN-based carbon fiber to woven into eight satin carbon cloth, with the warp at 0°, counterclockwise rotation to form +45°, 90° and -45°, and then cut into 300mm×300mm specifications Carbon cloth block spare;

[0053] 2) Laminate the carbon cloth blocks in step 1) in the order of 0 / +45 / 90 / -45 / 0, stack them to a thickness of 5mm, and stitch them along the thickness direction at a pitch of 4.0×4.0mm. Three-dimensional fabric, the fiber volume content is controlled at 50%;

[0054] 3) The carbon fiber three-dimensional fabric in step 2) is processed at 2200°C to form a preform, and the treatment process is: room temperature to 2200°C, 300°C / h; 2200°C, heat preservation for 2h; free cooling.

[0055] 4) The carbon fiber preform in step 3) is subjected to a chemical vapor deposition process. The deposition temperature is 980°C, the gas flow rate is 10L / min, the deposition chamber pressure is 1kPa, and the deposition time is 200h. After the process...

Embodiment 2

[0071] 1) Use general-purpose T300-3K PAN-based carbon fiber to woven into eight twill carbon fabrics, with the warp at 0°, counterclockwise rotation to form +45°, 90° and -45° respectively, and then cut into carbon according to the specifications of 300mm×300mm Cloth block spare;

[0072] 2) Laminate the carbon cloth blocks in step 1) in the order of 0 / 90 / +45 / 0 / 90 / -45, stack them to a thickness of 5mm and then follow the thickness direction at a pitch of 4.0×4.0mm Stitched to form a three-dimensional fabric, the fiber volume content is controlled at 50%;

[0073] 3) The carbon fiber three-dimensional fabric in step 2) is processed at 2200°C to form a preform, and the treatment process is: room temperature to 2200°C, 300°C / h; 2200°C, heat preservation for 2h; free cooling.

[0074] 4) Carry out the chemical vapor deposition process on the carbon fiber preform in step 3), the deposition temperature is 900℃, the gas flow rate is 6L / min, the deposition chamber pressure is 0.5kPa, the d...

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Abstract

The invention relates to a C / C-MC composite of a mixed matrix thermal structure and a preparation method thereof, in particular to a novel high-performance thermal structure composite for bearing and a preparation method thereof, and belongs to the technical field of carbon / carbon composite manufacturing. 45-degree fibers are introduced into the plane direction of carbon cloth laminated sewn structure textile, and on the basis of guaranteeing the stretching, compressing, bending and other performance of the material, the shearing performance of the material is improved, and the bearing performance of the material under complex loads is enhanced. By means of matching design of a complex matrix and introduction of the control technology and the fiber interface protection technology, the oxidation resistance of the material is improved, and integration of the bearing strength and heat-proof function of the material is achieved.

Description

Technical field [0001] The invention relates to a hybrid matrix thermal structure C / C-MC composite material and a preparation method thereof, in particular to a novel high-performance thermal structure composite material for bearing and a preparation method thereof, and belongs to the technical field of carbon / carbon composite material manufacturing. Background technique [0002] Carbon / carbon composite materials have excellent high temperature mechanical properties and thermal physical properties, such as high specific strength, high specific modulus, high thermal conductivity, low linear expansion coefficient, strong designability, thermal shock resistance, etc., especially the strength increases with temperature The feature of not falling but rising has always been one of the most important material solutions for key thermal protection components such as the tip, nozzle, cabin, and control rudder of strategic missile warheads in advanced countries. However, with the developmen...

Claims

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Application Information

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IPC IPC(8): C04B35/83C04B35/56C04B35/571
CPCC04B35/5622C04B35/571C04B35/83C04B2235/5248C04B2235/5256C04B2235/616
Inventor 冯志海张中伟李军平张国兵胡继东
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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