超高温陶瓷基复合材料设计制备和烧蚀机理

According to the requirements of two typical conditions (gliding and air-breathing hypersonic vehicles), the oxidative and ablative mechanisms were determined by means of experiments (ablation in static conditions of vacuum and air at high temperatures, ablation in dynamic conditions of arc-jet wind tunnel and flame from liquid rocket motor) and theoretical analysis of phase calculation. The contributions of various mechanisms to the ablation were also determined, and thus the prediction model for ablation was proposed. Based on the prediction model, the composite systems and anti-oxidative protective layers were designed and optimized, following ablative tests and validation. The achievements of this program will provide material support for preparation of the nose and leading edge of hypersonic vehicles.

根据两种典型的使用工况要求（滑翔式和吸气式高超声速飞行器），采用高温静态烧蚀（真空、空气）、高温动态烧蚀（发动机尾焰和电弧风洞）等多种试验手段和高温相图计算等理论分析方法，阐明两种超高温陶瓷基复合材料（C/SiC-ZrC和C/SiC-ZrB2）分别对应两种工况下的高温氧化/烧蚀机理，确定各种烧蚀机理的贡献程度，建立氧化/烧蚀机理预报模型。根据预报模型，设计优化超高温陶瓷基复合材料材料体系和抗氧化涂层，并通过典型工况下的试验进行烧蚀性能验证。项目的研究成果将为高超声速飞行器鼻锥、翼前缘等超高温部件的研制提供材料技术支撑。

根据两种典型的使用工况（滑翔式和吸气式高超声速飞行器）对耐超高温低烧蚀材料的需求，开展超高温陶瓷基复合材料的设计及制备工艺（先驱体转化和反应熔渗）研究，获得了系列的超高温陶瓷基复合材料。采用高温静态烧蚀（氧乙炔焰）、高温动态烧蚀（发动机尾焰和电弧风洞）等多种试验手段和高温相图计算等理论分析方法，阐明了超高温陶瓷基复合材料的高温氧化/烧蚀机理，建立氧化/烧蚀机理预报模型，确定超高温陶瓷基复合材料的服役使用温度区间。超高温陶瓷基复合材料经过典型服役环境的地面模拟考核，满足总体的设计技术指标要求，验证了其优异的综合性能。研究成果为高超声速飞行器的超高温结构部件的研制提供了关键的技术支撑。