UHTC-carbon fibre composites: Preparation, oxyacetylene torch testing and characterisation
UHTC-carbon fibre composites: Preparation, oxyacetylene torch testing and characterisation
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DOI：
10.1016/j.jeurceramsoc.2012.08.018
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发表时间：
2013-02-01
影响因子：
5.7
通讯作者：
Brown, P. M.
中科院分区：
文献类型：
--
作者：
Paul, A.;Venugopal, S.;Brown, P. M.
当前一代碳碳（C-C）和碳碳化硅（C- sic）材料的使用温度限制在1800摄氏度以下，并且寻求能够承受更高温度和烧蚀条件的材料用于航空航天应用。一种潜在的材料解决方案是碳纤维基复合材料，其基体由一个或多个超高温陶瓷（UHTCs）组成；后者的目的是在高温下保护碳纤维，而前者为整个系统提供了更高的韧性和抗热震性。采用浆料浸渍热解法制备了碳纤维- uhtc粉末复合材料。采用ZrB2、ZrB2-20 vol% SiC、ZrB2-20 vol% SiC-10 vol% LaB6、HfB2和HfC五种不同的UHTC组合物进行浸渍。在2500℃以上的高温条件下，利用专门建造的氧乙炔炬测试设备对其高温抗氧化性进行了研究，并与C-C基准复合材料的结果进行了比较。(C) 2012 Elsevier Ltd.版权所有。
Current generation carbon carbon (C-C) and carbon-silicon carbide (C-SiC) materials are limited to service temperatures below 1800 degrees C and materials are sought that can withstand higher temperatures and ablative conditions for aerospace applications. One potential materials solution is carbon fibre-based composites with matrices composed of one or more ultra-high temperature ceramics (UHTCs); the latter are intended to protect the carbon fibres at high temperatures whilst the former provides increased toughness and thermal shock resistance to the system as a whole. Carbon fibre-UHTC powder composites have been prepared via a slurry impregnation and pyrolysis route. Five different UHTC compositions have been used for impregnation, viz. ZrB2, ZrB2-20 vol% SiC, ZrB2-20 vol% SiC-10 vol% LaB6, HfB2 and HfC. Their high-temperature oxidation resistance has been studied using a purpose built oxyacetylene torch test facility at temperatures above 2500 degrees C and the results are compared with that of a C-C benchmark composite. (C) 2012 Elsevier Ltd. All rights reserved.