为进一步满足新一代火箭、高推比航空发动机、临近空间飞行器用轻质耐高温材料应用需求，针对C/C-ZrC-SiC复合材料烧蚀后氧化物保护膜抗热震性能差、易脱落等缺点，拟将ZrB2-ZrC-SiC超高温陶瓷引入到C/C复合材料中，以优化氧化物保护膜的结构与性能；同时将SiC纳米线引入到ZrB2-ZrC-SiC陶瓷基体中，以提高氧化物保护膜的结合、抗热震、抗冲刷能力，从而延长材料在动态循环条件下的使用寿命。通过SiC纳米线增韧对材料微观结构和抗氧化耐烧蚀性能影响规律研究，初步建立SiC纳米线增韧材料的抗氧化耐烧蚀机理与模型。针对材料在高温循环热震条件的抗氧化耐烧蚀性能考核，研究高温循环热震环境下，SiC纳米线增韧材料的抗氧化耐烧蚀机理模型，为材料在高温动态热震环境下的服役提供参考依据。通过项目实施，为新一代火箭、高推比航空发动机、临近空间飞行器用轻质耐高温热防护材料的制备与应用打下良好的技术基础。

To meet the increasing demand for light-weight and high-temperature structural materials that capable of operation over 2000 C for new generation rocket, high thrust loading aero-engine and near space vehicle application, and to further improve the bonding ability and thermal shock resistance of the self-healing protection film for C/C-ZrC-SiC composites. The ZrB2-ZrC-SiC ultra high temperature ceramics were introduced into C/C composites to optimize the composition and structure of the formed self-healing protection film and improve its performance. Meanwhile, SiC nanowires are added into the ZrB2-ZrC-SiC ceramic matrix to improve the bonding ability, thermal shock resistance and anti-scour ability of the self-healing protection film under cyclic thermal shock condition. Therefore, the service life of the C/C-ZrC-SiC composites under cyclic thermal shock oxidation and ablation environment can be extended via the above two proposals. The effect of SiC nanowires addition on structure and anti-oxidation and ablation properties of the C/C-ZrB2-ZrC-SiC composites will be investigated, and then the anti-oxidation and ablation mechanisms of the SiC nanowire toughened composites will be analyzed. Through the anti-oxidation and ablation tests under the cyclic thermal shock condition at high temperatures, the anti-oxidation and ablation mechanisms of the SiC nanowire toughened composites in cyclic thermal shock condition will be established, which will offer valuable suggestions and application foundation for C/C-ZrB2-ZrC-SiC composites served in cyclic thermal shock environment. The accomplishment of this project will also provide good foundation for fabrication and application of the C/C-ZrB2-ZrC-SiC composites that are used on new generation rocket, high thrust loading aero-engine and near space vehicle.