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Ceramic-based composite coating and preparation method thereof

A ceramic matrix composite and coating technology, applied in coatings, fireproof coatings, etc., can solve the problems of component failure, affecting the normal use of materials, and falling off.

Active Publication Date: 2016-06-01
CHINA ACADEMY OF ENG PHYSICS FUNCTION MATERIAL RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the difference in thermal physical properties between the coating and the C / C composite material, the thermal stress generated will inevitably cause the coating to crack and fall off. The destruction of the coating may cause the carbon fiber to be exposed to the gas environment, and the oxidation of the carbon fiber will cause the failure of the component. , seriously affect the normal use of the material

Method used

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  • Ceramic-based composite coating and preparation method thereof
  • Ceramic-based composite coating and preparation method thereof
  • Ceramic-based composite coating and preparation method thereof

Examples

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preparation example Construction

[0043] Such as figure 1 Shown, the preparation method of the ceramic matrix composite coating of one embodiment, comprises the following steps:

[0044] Step S10: by mass ratio (1%-99%): (1%-99%): (1%-99%) containing alkyne group resin, polyborosilazane and / or polysilazane resin, The filler is mixed uniformly, wherein the mass sum of the alkyne-containing resin, the polyborosilazane and / or polysilazane resin, and the filler is 100%;

[0045] Step S20: adding an organic solvent to the above mixture for dilution, and coating or impregnating the carbon fiber after grinding and dispersing;

[0046] Preferably, the solvent is at least one of toluene, xylene, n-hexane, cyclohexane, and n-heptane.

[0047] Step S30: The product obtained after step S20 is cured and cross-linked at 100°C-400°C, and then pyrolyzed at 900°C-1800°C in an inert atmosphere to form the high temperature resistant ceramic matrix composite coating.

[0048]Experiments have proved that when the alkynyl conten...

Embodiment 1

[0053] Polysilazane 12g (44%) was diluted with a certain amount of toluene, propargyl phenolic resin 12g (44%) was diluted with a certain amount of toluene, mixed evenly, and then added ZrO 150nm ground in advance 2 3g powder (12%), mix and stir to disperse evenly, take a certain amount of carbon fiber and immerse in the mixed liquid, take it out of the oven and cure it at 150°C for 2h, and in Ar atmosphere, pyrolyze it at 1300°C (heating rate: 10°C / min) for 2h , XRD analysis of pyrolysis products found that SiBNC, ZrO 2 (t,m) and free C generation.

Embodiment 2

[0055] Polysilazane 15g (75%) was diluted by adding a certain amount of xylene, aryl acetylene resin 3g (15%) was diluted by adding a certain amount of toluene, mixed uniformly, then added 2g (10%) of ZrC powder that had been ground in advance to 200nm, mixed Stir and disperse evenly, take a certain amount of carbon fiber and immerse it in the mixed solution, take it out of the oven and solidify at 200°C for 1.5h, A is pyrolyzed in Ar atmosphere at 900°C (heating rate is 5°C / min) for 2h, and analyze the pyrolysis products. In addition to ZrC, there are also SiNC and free C generation.

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Abstract

The invention provides a ceramic-based composite coating. Alkynyl-containing resin, polyborosilazane and / or polysilazane and a filling material serve as main raw materials, and are diluted by a proper organic solvent to obtain a solution; the solution is coated or immersed on a C / C material after being grinded and dispersed, and is then subjected to curing cross-linking and high temperature pyrolysis to form a high temperature-resistant ceramic-based composite coating. According to the ceramic-based composite coating provided by the invention, as alkynyl is contained in a precursor, not only temperature of the curing cross-linking can be reduced, but also more free carbons can be formed during the high temperature pyrolysis, and are helpful to form indissolvable metallic carbide and SiC; the formation of the carbide can enhance the interface adhesive strength between the ceramic-based composite coating and a carbon material, and can have dual high temperature-resistant advantages of both high temperature silicon carbonitride or silicon-boron carbonitride ceramic and a metallic carbide material. Moreover, the service life of base materials under severe environments such as high temperature, ablation and the like is prolonged, and the ceramic-based composite coating can be used to solve the problem on surface oxidation resistance of a thermal ablation resistant material.

Description

technical field [0001] The invention relates to the technical field of functional materials, in particular to a ceramic matrix composite coating and a preparation method thereof. Background technique [0002] In recent years, with the development of aerospace technology, space power has become the main force for implementing national security and military strategies in the 21st century. During the re-entry process of the spacecraft, due to the strong aerodynamic heating, the temperature of the nose cone and the leading edge of the wing can reach as high as 1650°C. The thermal protection system is one of the four key technologies of the spacecraft. Carbon / carbon (C / C) composite material is a composite material of carbon fiber reinforced carbon matrix. It has a series of excellent properties such as high strength, corrosion resistance, good friction resistance, and good chemical stability. It is a new type of ultra-high temperature composite material. It can withstand a stag...

Claims

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Application Information

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IPC IPC(8): C09D183/16C09D161/06C09D179/04C09D7/12
CPCC08K2201/011C08L2201/08C09D5/18C09D7/61C09D161/06C09D179/04C09D183/16C08L61/06C08K2003/2244C08L83/16C08L49/00C08K3/14C08K3/22
Inventor 刘键林德苗吴佩萱王真
Owner CHINA ACADEMY OF ENG PHYSICS FUNCTION MATERIAL RES INST
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