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A kind of preparation method of high temperature and anti-oxidation light weight carbon/carbon heat insulation material

A technology of thermal insulation material and high temperature oxidation, applied in the field of inorganic thermal insulation materials, can solve the problems of low temperature resistance grade and high temperature oxidation resistance of carbon fiber thermal insulation materials, and achieve the effect of wide application environment

Active Publication Date: 2018-11-23
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

[0003] The technical problem solved by the invention: to overcome the problems of low temperature resistance level of existing ceramic fiber heat insulation materials and high temperature oxidation resistance of carbon fiber heat insulation materials, and provide a preparation method of high temperature resistant and oxidation-resistant lightweight carbon / carbon heat insulation materials, Realize the preparation of high temperature resistant (above 1500°C) oxidation-resistant lightweight carbon / carbon insulation materials

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] 1) Mix short-cut viscose-based carbon fibers with a length of 5mm and phenolic resin at a weight ratio of 1:2, stir to form a uniform material, then filter it in the mold, remove excess resin, cure at 150°C, and then In the range of 700 ° C ~ 2000 ° C, the temperature is programmed for carbonization to obtain C f / C r bulk material.

[0026] 2) Add C f / C r The bulk material is placed in chemical vapor infiltration equipment, using propylene as the carbon source, and reacting the coating at 1000 ° C for 20 hours to obtain the C of the carbon coating. f / C r bulk material.

[0027] 3) C of the carbon coating f / C r The bulk material is deposited on the surface of the carbon coating at 1050 ° C for 30 h in a chemical vapor deposition furnace, using chlorosilane as a precursor to form a silicon carbide coating.

[0028] 4) Coat the surface of the above material with resin slurry added with silicon carbide powder and silicon powder, and then sinter at 1500°C. A sur...

Embodiment 2

[0031] 1) Mix chopped polyacrylonitrile-based carbon fibers with a length of 20 mm and furfurone resin at a ratio of 1:0.8, and then knead to form a uniform mud. Then carry out compression molding in the mold, then solidify at 180°C, and then carry out carbonization by temperature programming in the range of 700°C to 1800°C to obtain C f / C r bulk material.

[0032] 2) Add C f / C r The bulk material is placed in chemical vapor infiltration equipment, using methane as the carbon source, and reacting the coating at 1000 °C for 80 hours to obtain the C of the carbon coating. f / C r bulk material.

[0033] 3) C of the carbon coating f / C r The bulk material is placed in a vacuum evaporation equipment, and the mixed powder containing silicon powder, silicon dioxide powder and silicon carbide powder is used as the gas phase silicon source material, and heated to 1600 °C at 2kPa to make the silicon and silicon monoxide produced steam into C f / C r In the bulk material, reac...

Embodiment 3

[0037] 1) Mix chopped pitch-based carbon fibers with a length of 40mm and phenolic resin at a ratio of 1:1.5, add an appropriate amount of ethanol and stir vigorously to form a uniform slurry. Then carry out pressure filtration molding in the mold to remove excess resin, then solidify at 180°C, and then carry out carbonization at a temperature programmed within the range of 700°C to 1600°C to obtain C f / C r bulk material.

[0038] 2) Add C f / C r The bulk material is placed in chemical vapor infiltration equipment, using propane as a carbon source, and reacting the coating at 1000 ° C for 40 hours to obtain the C of the carbon coating. f / C r bulk material.

[0039] 3) C of the carbon coating f / C r The bulk material is placed in a vacuum evaporation equipment, and the mixed powder containing silicon powder, silicon dioxide powder, alumina powder and silicon carbide powder is used as the gas phase silicon source material, and heated to 1650 °C under 10kPa to make the p...

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Abstract

The invention relates to a preparation method of a high-temperature-resistant and oxidation-resistant lightweight carbon / carbon thermal insulation material, belongs to the field of inorganic thermal insulation material, and is mainly used for providing the preparation method of the thermal insulation material capable of achieving thermal protection in a high-temperature aerobic environment. With short-cut carbon fibers as a reinforcing body and resin carbon as a matrix, a porous material is formed by kneading, sizing, curing and carbonization treatment; a continuous carbon plating layer is formed on pore walls by a chemical vapor infiltration method, and the internal fibers and the matrix are protected; a silicon carbide coating layer is formed on the surface of the carbon plating layer in pore gaps by a gas phase method, a formation temperature is controlled, and microcrystalline silicon carbide is formed; a dense layer is formed by a surface densification technology, a high-temperature oxidation protection coating layer is prepared on the surface of the dense layer, and the high-temperature-resistant and oxidation-resistant lightweight carbon / carbon thermal insulation material is formed.

Description

technical field [0001] The invention relates to a preparation method of a high-temperature-resistant and anti-oxidation light carbon / carbon heat insulating material, which belongs to the field of inorganic heat insulating materials. Background technique [0002] The thermal protection system of aerospace vehicles is the key to ensure its supersonic flight, and lightweight thermal protection materials are an important direction for the development of modern aerospace vehicles. Porous insulation materials made of ceramic fibers (such as quartz fibers and mullite fibers) have been widely used in the space shuttle thermal protection system. The temperature resistance grade of quartz fiber is low. At high temperature (over 1200°C), it is prone to fiber crystallization and sharp decline in mechanical properties, making it unusable. As a result, ceramic tiles formed of quartz fiber can only be used below 1100°C. The temperature resistance level of ceramic tiles can be improved by ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/83C04B35/622
CPCC04B35/622C04B35/83C04B2235/3826C04B2235/48C04B2235/5248C04B2235/526C04B2235/614
Inventor 李同起冯志海张大海
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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