高超声速飞行器中某些关键部位(如燃烧室局部喷射装置、发动机热端)通常都在高热流和超高温环境下工作，现有的热防护材料很难满足使用要求。主动冷却防热是在高热流和超高温环境下保护防热材料或部件的安全使用的重要方法和必有之路。.本项目以主动冷却用定向孔、高强度、超高温多孔陶瓷为研究对象，拟通过耐超高温、定向孔和高强度ZrB2基陶瓷材料体系的选择和优化、定向孔结构设计和性能调控，通过相应的制备工艺优化，制备出耐超高温、定向孔、高强度多孔陶瓷材料，并揭示材料体系-微结构-热力性能之间的内在联系，获得主动冷却定向孔超高温陶瓷材料的微结构控制方法和相应热力匹配规律，为该类材料在高超声速飞行器主动冷却部件提供研究基础和技术支持。

Many important components(i.e.,injection device and hot section for local site in combustion chamber and engine) of hypersonic vehicle usually serves in high heat flux and ultra-high temperature environment, so the existing thermal protection materilas can hardly satisfy requirements for the use. Active cooling for TPS is an important and only way to protect thermal protection materilas or components serving safely in high heat flux and ultra-high temerature..According to the requirement of aligned, high-strength and ultra-high temperature porous cermaics, this project aims to optimize and select ZrB2-based aligned and high-strength porous ceramics, microstructural design and properties controlling. We will prepare ZrB2-based porous ceramics with ultra-high temperature resistance, aligned pore distribution and high mechanical strength using the corresponding fabricating process optimization. An internal relationship among the materials system, microstructure and thermo-mechanic properties will be clarified and explained. Microstructural controlling method and relevant thermo-mechanic matching law for active cooled aligned ZrB2-based porous ceramics will be acquired through this project study. The research achievements of this project will supply research foundation and technical support for such special porous ceramics in the field of hypersonic vehicle.