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Ceramic composite material of high temperature insulation sandwich structure and method for preparing ceramic composite material

A ceramic composite material and a composite material technology are applied in the field of high temperature resistant and heat insulating sandwich structure ceramic composite materials and their preparation, which can solve the problems of difficult to solve the problem of thermal expansion and thermal stress of panels, and difficult to accurately control the surface shape accuracy of ultra-thin panels. The effect of improving the thermal insulation effect, improving the mechanical properties, and improving the installation method

Active Publication Date: 2014-11-12
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are many unresolved problems in this structure in China. First, the high temperature resistant thermal bridge blocking connection structure has not been solved. Second, the thermal expansion of the panel will cause serious thermal stress and many problems arising therefrom are difficult to solve. Third, the ultra-thin It is difficult to accurately control the surface accuracy of the panel

Method used

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  • Ceramic composite material of high temperature insulation sandwich structure and method for preparing ceramic composite material
  • Ceramic composite material of high temperature insulation sandwich structure and method for preparing ceramic composite material

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Embodiment 1

[0028] The high-temperature-resistant heat-insulating sandwich structure ceramic composite material of the present embodiment, the core layer is the silica airgel composite material layer that mullite short fiber strengthens, and the thickness of core layer is 20mm; The density of core layer material is 0.32g / cm 3 , the thermal conductivity is 0.028W / m×K; the upper and lower surfaces of the core layer are compounded with quartz fiber cloth reinforced silica ceramic composite surface plates, the thickness of the upper surface plate is 1mm, and the thickness of the lower surface plate is 0.5mm.

[0029] The preparation method includes the following steps: (1) selecting mullite short fiber reinforced silica airgel composite material as the core layer material, and the core layer material is prepared by supercritical drying method (refer to Chinese patent 200510031952.0, 200710034510.0, 201110110844.8, 201110110947.4, 201110110946.X, 201010300112.0 or 201010148105.3 by the disclo...

Embodiment 2

[0034] The high-temperature-resistant and heat-insulating sandwich-structure ceramic composite material of this embodiment has a core layer of alumina airgel composite material layer reinforced by alumina short fibers, and the thickness of the core layer is 25mm; the density of the core layer material is 0.35g / cm 3 , the thermal conductivity is 0.032W / m×K; the upper and lower surfaces of the core layer are compounded with silicon carbide fiber cloth reinforced alumina ceramic composite surface plates, and the thickness of the upper and lower surface plates is 0.9mm respectively.

[0035]The preparation method includes the following steps: (1) selecting alumina short fiber reinforced alumina airgel composite material as the core layer material, and the core layer material is prepared by supercritical drying method (refer to Chinese patents 200510031952.0, 200710034510.0, 201110110844.8, 201110110947.4, 201110110946.X, 201010300112.0 or 201010148105.3 published methods), the thic...

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Abstract

Disclosed are a ceramic composite material of a high temperature insulation sandwich structure and a method for preparing the ceramic composite material. A core layer of the composite material is an aerogel composite material layer reinforced by high temperature resistant inorganic fibers, oxide ceramic composite material surface plates reinforced by high temperature resistant inorganic fibers are compounded on the upper surface and the lower surface of the core layer, the thickness of the core layer is larger than or equal to 2mm, and the thicknesses of the upper surface plate and the lower surface plate respectively range from 0.1mm to 3.0mm. The method for preparing the ceramic composite material of the high temperature insulation sandwich structure includes the steps: (1) selecting aerogel composite materials reinforced by the high temperature resistant inorganic fibers as materials of the core layer with the thickness larger than or equal to 2mm; (2) tiling high temperature resistant inorganic fiber cloth or thin-layer fabrics on the upper surface and the lower surface of the core layer to perform needling, puncture or sewing; (3) sucking sol in a vacuum manner and gelating the sol at the temperature of 30-200 DEG C; and (4) performing heat treatment. The ceramic composite material of the high temperature insulation sandwich structure integrates the functions of heat insulation, bearing, wave penetration and the like.

Description

technical field [0001] The invention relates to a high-temperature-resistant and heat-insulating ceramic composite material and a preparation method thereof, in particular to a high-temperature-resistant and heat-insulating sandwich-structure ceramic composite material and a preparation method thereof. Background technique [0002] High-speed aircraft such as spaceships or returnable satellites fly in the atmosphere at high speed for a long time, and the temperature of a large area exceeds 600°C, and some parts reach 1400°C. The "large area" referred to here generally accounts for more than 80% of the outer layer area of ​​the aircraft. Ceramic insulation tiles have played an important role in the US space shuttle and seem to be mature, but they are inherently brittle (the toughness is generally 1-5MPa×m 1 / 2 ), low strength (bending strength is generally less than 5MPa), high thermal conductivity (generally greater than 0.06W / m×k), and small single-piece area (generally 200...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B32B18/00B32B37/06B32B37/10B32B37/12C04B35/82C04B35/80C04B35/622
Inventor 曹峰冯坚姜勇刚张长瑞
Owner NAT UNIV OF DEFENSE TECH
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