Abstract Thermal protection systems with long time anti-ablation property for applications in ultrahigh temperature environments have been a choke point for the development of hypersonic vehicles. In the present work, new ZrC-SiC-TiC ternary composite coatings were designed and fabricated by vacuum plasma spray. The ablation behaviors of the ternary coatings were evaluated by a plasma flame with temperatures about 2200−2500 °C and compared with the ZrC-SiC and ZrC-TiC composite coatings. The characteristics of phases, element distributions and microstructure of the oxidized layers were observed in detail. The results showed that the anti-ablation resistant property of the ternary coatings was much better than those of the ZrC-SiC and ZrC-TiC composite coatings. The oxidation products, like high viscous SiO2 and high thermo stable TiO2, played a mutual promoted role in modifying the oxide layers, which contributing a lot to the improved ablation resistance. The ablation mechanisms of the ZrC-SiC-TiC ternary coatings were analyzed based on microstructure observations and thermodynamic analysis.

中文翻译：

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设计的 ZrC-SiC-TiC 三元涂层在 2000 oC 以上环境中的长时间烧蚀行为

摘要 用于超高温环境的具有长时间抗烧蚀性能的热保护系统一直是高超音速飞行器发展的瓶颈。在目前的工作中，新型 ZrC-SiC-TiC 三元复合涂层的设计和制造采用真空等离子喷涂。三元涂层的烧蚀行为通过等离子火焰进行评估，温度约为 2200-2500 °C，并与 ZrC-SiC 和 ZrC-TiC 复合涂层进行比较。详细观察了氧化层的物相特征、元素分布和微观结构。结果表明，三元涂层的抗烧蚀性能明显优于ZrC-SiC和ZrC-TiC复合涂层。氧化产物，如高粘度 SiO2 和高热稳定性 TiO2，在氧化层改性方面起到了相互促进的作用，这对提高抗烧蚀性有很大贡献。基于微观结构观察和热力学分析，分析了ZrC-SiC-TiC三元涂层的烧蚀机理。