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Preparation method of C/C-SiC (carbon/carbon-silicon carbide) composite material vacuum heat insulation plate

A technology of vacuum insulation panels and composite materials, which is applied in the field of preparation of C/C-SiC composite material vacuum insulation panels, can solve the problems that vacuum insulation panels cannot be used in high temperature environments, and achieve the effect of low thermal conductivity

Active Publication Date: 2016-06-08
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to overcome the problem that traditional vacuum insulation panels cannot be used in high temperature environments, and provide a C / C-SiC composite material that can be used at high temperatures and has extremely low thermal conductivity Preparation method of vacuum insulation panel

Method used

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  • Preparation method of C/C-SiC (carbon/carbon-silicon carbide) composite material vacuum heat insulation plate

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0014] (1) A layer of graphite paper is coated on the outer surface of the ceramic fiber core material, the thickness of the graphite paper is 100 μm, and the porosity of the core material is 90%:

[0015] (2) Wrap the carbon fiber shell on the surface of graphite paper to form a prefabricated part. The carbon fiber shell is composed of carbon fiber prepreg cloth, and the thickness of the prefabricated body is 3mm;

[0016] (3) Put the prefabricated part into a vacuum chemical vapor deposition furnace, raise the temperature to 1100°C, pass in propylene, hydrogen, and argon, and through chemical vapor phase infiltration, the shell becomes a C / C composite material skeleton, and the porosity of the shell is 10%;

[0017] (4) Using molten silicon infiltration method, put the prepared sample into a graphite crucible, embed it with Si powder, put the crucible into a vacuum furnace for heating, the heating rate of the vacuum furnace is 10°C / min, and the vacuum degree in the furnace i...

Embodiment 2

[0023] (1) Coating a layer of graphite paper on the outer surface of the ceramic fiber core material, the thickness of the graphite paper is 50 μm, and the porosity of the core material is 80%;

[0024] (2) Weave a carbon fiber shell on the surface of graphite paper to form a prefabricated part, and the thickness of the prefabricated body is 5mm;

[0025] (3) Put the prefabricated part into a vacuum chemical vapor deposition furnace, raise the temperature to 1000°C, pass in methane, hydrogen, and argon, and through chemical vapor phase infiltration, the shell becomes a C / C composite material skeleton, and the porosity of the shell is 10%;

[0026] (4) Using molten silicon infiltration method, put the prepared sample into a graphite crucible, embed it with Si powder, put the crucible into a vacuum furnace for heating, the heating rate of the vacuum furnace is 10°C / min, and the vacuum degree in the furnace is 1Pa, the reaction temperature is 1500°C, and the reaction time is 1h,...

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Abstract

The invention discloses a preparation method of a C / C-SiC (carbon / carbon-silicon carbide) composite material vacuum heat insulation plate. The preparation method comprises the following steps of firstly, preparing a layer of carbon fiber preform at the surface of a heat insulation core coated with graphite paper; then, preparing a layer of pyrolytic carbon at the surface of the carbon fiber by a chemical vapor phase infiltration method; putting a prepared sample into a graphite crucible by a melting silicon infiltration method, coating by Si (silicon) powder, and putting the crucible into a vacuum furnace to heat, wherein the reaction temperature is 1450-1550 DEG C; depositing a SiC layer by the chemical vapor phase infiltration method to fill and seal the remained microcracks; finally, forming a small circular hole in the bottom part of a composite material outer casing, and filling and sealing the small hole with melt under a vacuum environment, so as to obtain the C / C-SiC composite material vacuum heat insulation plate. The C / C-SiC composite material vacuum heat insulation plate prepared by the preparation method can be used in the environment with the temperature higher than 1500 DEG C, and the heat conductivity coefficient is lower.

Description

technical field [0001] The invention relates to a preparation method of a heat insulation board, in particular to a preparation method of a C / C-SiC composite material vacuum heat insulation board. Background technique [0002] The new high-speed spacecraft has the characteristics of short response time and rapid global arrival. It is one of the focuses of space technology research that the world's aerospace powers are competing to carry out. The flight speed of some new high-speed aerospace vehicles can reach Mach 10, and the flight time can reach tens of minutes. Coupled with the space constraints brought about by the compact airframe structure, it poses an unusual challenge to the thermal protection system. The heat insulation material used in the thermal protection system must have the performance characteristics of ultra-high temperature resistance, ultra-low thermal conductivity and sufficient strength at the same time, so as to effectively block the heat from the surf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/573C04B35/83
CPCC04B35/573C04B35/83C04B2235/5248C04B2235/5256C04B2235/614
Inventor 陈照峰汪洋余盛杰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS