超高温陶瓷基复合材料的改性和烧蚀行为  

Modification and Ablation Behaviors of Ultrahigh Temperature Ceramic Matrix Composites

作　　者：段刘阳 罗磊[1] 王一光[1] 

机构地区：[1]西北工业大学超高温结构复合材料重点实验室,陕西西安710072

出　　处：《中国材料进展》2015年第10期762-769,782,共8页Materials China

摘　　要：高超音速飞行器热防护系统需要超高温陶瓷基复合材料,基于C/SiC复合材料的涂层和基体耐高温、抗烧蚀改性是制备超高温陶瓷基复合材料的有效方法。简述了C/SiC复合材料的制备方法和烧蚀性能,并在此基础上综述了超高温陶瓷单一组元和多元复合组元对C/SiC复合材料涂层及基体改性的研究进展及其烧蚀行为,指出难熔金属硼化物和碳化物,如ZrB2、ZrC、TaC、HfC等单一或复合组元,可有效提高C/SiC复合材料高温抗氧化和抗烧蚀性能。针对未来往返飞行器对材料重复烧蚀的需求,初步阐述了基于C/SiC复合材料的超高温陶瓷基复合材料改性方法,并给出了在氧乙炔焰下重复烧蚀结果。The development of hypersonic vehicles requires ultrahigh temperature ceramic matrix composites （ UHTC- MCs） for their thermal protection system. The effective way to fabricate the UHTCMCs is to enhance the ablation resist- ance of coatings and matrix of C/SiC composites. In this paper, we briefly introduced the fabrication of C/SiC composites and their ablation behaviors. The modification of the coatings and matrix of C/SiC composites by adding single- or multi- UHTC components was reviewed, and their ablation behaviors as well, The results indicated that the refractory borides or carbides, such as ZrB2 , ZrC, TaC and HfC, which were good candidates to enhance the high temperature resistance and the ablation resistance. Base on the requirements of multiple ablation resistance for future reentry vehicles, the modifica- tion of UHTCMCs to meet these requirements was also reported. The preliminary results of multiple ablation under oxyacet- ylene torch flame were given.

关 键 词：超高温陶瓷基复合材料 涂层改性 基体改性 烧蚀 

分 类 号：TB332[一般工业技术—材料科学与工程]