高焓气流作用下超高温材料微结构损伤机理与性能演化模型

本项目针对航天飞行器非烧蚀热防护系统中高焓高速气流与热防护材料传热传质耦合作用机制这一核心科学问题，以碳/碳化硅、二硼化锆/碳化硅等典型超高温非烧蚀复合材料为研究对象，聚焦高焓气流作用下防热材料高温催化、多机制氧化与微结构演化定量预测难题，开展高焓非平衡气体与超高温复合材料催化反应建模、多组分复合材料氧化机制以及多尺度传热耦合机理研究，揭示高焓气体表面催化与高温氧化极端环境下材料微细观结构演化机制；建立材料热化学损伤演化与传热耦合计算模型并完成等离子风洞实验验证，发展基于高焓风洞平台的超高温材料重复使用性能实验评价表征方法，实现超高温复合材料热化学与传热性能的定量准确预测，为天地往返航天飞行器非烧蚀热防护材料创新研制与科学评价奠定基础。

This proposal focuses on the coupled heat and mass transfer phenomena from the high velocity and high enthalpy air flow hitting upon Ultra-high Temperature Materials (UHTMs) using by Reusable Launch Vehicles (RLVs). C/SiC and fiber reinforced ZrB2/SiC UHTMs are chosen as representative materials and experimental samples. Making appropriate approachs to solve the problems that are difficult to accurately predict microstructure evolution/damage accumulation and chemical damage. Characteristic chemical/physical insight such as high enthalpy atomic gases catalysis, complex chemical reactions by multi-compositions, meso-porous structure evolution and their coupled effects requires special concern. All coupled heat and mass effects of above studies are considered to discover the mechanism of multi-scale heat and mass transfer. A theoretical model to reflect catalytic recombination of high-enthalpy non-equilibrium gas atoms on different materials will be constructed after verified by the plasma wind tunnel experiments. Then, on-ground testing standards to calibrate UHTM’s reusable performance will be proposed according to theoretical analysis, numerical computations and the plasma wind tunnel capability. Computational models can quantitatively predict microstructure evolution/damage accumulation process and evaluate thermo-chemical properties of UHTMs. Achievements about theoretical models or experimental methodology will found a set of design, characterization and evaluation infrastructure for non-ablative thermal protection materials used in RLVs.