高超飞行器用C/SiC-ZrC复合材料力学及烧蚀性能研究  

Mechanical properties and ablation properties of C/SiC-ZrC composites for hypersonic vehicle

作　　者：杨晓辉[1] 王芙愿 王毅[1] 曹佩[1] 白龙腾[1] 赵强[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2017年第3期59-66,共8页Journal of Rocket Propulsion

摘　　要：以PZC为有机锆先驱体原材料,采用A,B,C三种PIP工艺路线制备了不同ZrC含量的C/Si C-ZrC复合材料,并对C/Si C-ZrC复合材料的组成、微观结构、力学性能、烧蚀性能及作用机理进行了测试和分析。结果表明,有机锆先驱体制备的C/Si C-ZrC复合材料烧蚀性能有大幅提高,但其力学性能却存在一定程度的下降,并且随着ZrC含量的增加,C/SiC复合材料的力学性能呈现出逐渐降低的趋势,其质量烧蚀率和线烧蚀率呈现出先减小后增大的趋势。Taking PZC as the raw material of organic zirconium precursor, C/SiC-ZrC composites with different ZrC content were prepared by three PIP processes. The composition, microstrueture, mechanical properties, ablative properties and mechanisms of the C/SiC-ZrC composites were tested and analyzed. The results showed that the ablative properties of C/SiC-ZrC composites prepared with the organic zirconium precursor have been improved greatly, but its mechanical performance has a certain degree of decline, and with the increase of ZrC content, the mechanical properties of C/SiC composites decreased gradually, but its mass ablation rate and linear ablation rate appear as decreasing trend at first and then increasing trend.

关 键 词：C/SiC-ZrC复合材料 有机锆先驱体 力学性能 烧蚀性能 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]