先驱体转化法制备2D C/SiC-ZrC复合材料中ZrC含量对材料结构性能影响研究

Effects of ZrC Content on Microstructure and Properties of 2D C/SiC-ZrC Composites via Precursor Infiltration and Pyrolysis

针对高超音速飞行器、可重复使用运载器和下一代火箭发动机等超高温使用环境的工况要求,提出在2D C/SiC复合材料中引入耐超高温ZrC填料。采用先驱体转化法制备了不同ZrC含量的2D C/SiC-ZrC新型复合材料,考察了ZrC含量对材料力学性能、抗烧蚀性能和组成结构的影响。结果表明,材料的弯曲强度和弯曲模量随着ZrC含量的增加有一定程度的下降,材料的抗烧蚀性能明显提高,其中ZrC含量最高(33.3vol%)的试样S-50弯曲强度和弯曲模量均最低,分别为192.1MPa和27.5GPa;经氧乙炔焰烧蚀考核60s后,表面温度达到2123℃,试样表现出最低的烧蚀率,线烧蚀率为0.004mm/s,质量烧蚀率为0.006g/s。

According to the working requirements of hypersonic spacecrafts, reusable space vehicles and next generation rocket engines operating at ultra-high temperature condition, a proposal to improve anti-ablative property of 2D C/SiC composites by introduction of ZrC filler was presented. 2D C/SiC-ZrC composites with different ZrC contents were prepared via precursor infiltration and pyrolysis （PIP） process, and acclordingly the influence of ZrC contents upon the mechanical, anti-ablative,structural properties and compositions of 2D C/SiC-ZrC composites were investigated. The results were that flexural strength and flexural modulus of composites decreased with ZrC content increase, but the anti-ablative properties were greatly improved. The sample S-50 with the highest ZrC content （33.3 vol % ） has the lowest ~qexural strength of 192.3 MPa and flexural modulus of 27.5GPa. After ablation for 60 seconds in oxya- cetylene torch environment, the surface temperature of sample S-50 was as high as 2123℃. The sample S-50 showed the best anti-ablative property, and mass loss rate and linear recession rate were as low as 0. 006g/s and 0. 004mm/s, respectively.