X-43A高超音速飞行器C/C热防护涂层结构分析

Thermal protection coatings of C/C composites in X-43A hypersonic vehicles

介绍了涂层式抗氧化C/C复合材料在美国的研制及其在高超音速飞行器上应用概况,重点是C/C复合材料抗氧化复合涂层的涂层结构、制备工艺和应用评价。C/C复合材料表面化学转化法生成Si C过渡层是美国航天飞行器制备抗氧化涂层的通用方法。MER公司研制的转换法Si C、化学气相沉积Si C和Hf C 3层涂层结构的抗氧化C/C复合材料,其横向压缩性能大于未涂层C/C材料;并成功地应用于X-43A Ma10飞行器2 200℃的临近空间飞行,实现了零氧化烧蚀。

This paper describes the research developments of anti-oxidation C/C composites with multi-layered coatings and its applications in American hypersonic vehicles. The coatings structure and fabrication technologies, as well as validation performances, are especially introduced. A SiC bond coating derived by chemical vapor reac- tion （CVR） is generally adapted in fabricating the anti-oxidation C/C composites for aerospace vehicles. MER Cor- poration manufactured the X-43A Mach-10 vehicle C/C nose leading edges with a three-layer coatings composed of CVR-SiC, chemical vapor deposition （CVD） SiC and a thin layer CVD-HfC. The multi-layered C/C composites havehigher compression strength than that of uncoating specimen, and successfully survived the 2 200℃ extreme temperature near-space hypersonic flight with zero oxidation ablation.