摘要
通过反应熔渗(RMI)方式,以缝合碳纤维预制体和Si-Zr合金作为反应物,制备得到C_(f)/C-ZrC-SiC复合材料,并利用SEM-EDS和XRD系统分析了复合材料的微观结构,可以明确SiC-ZrC陶瓷基体在材料内部分布比较均匀且致密度较高。得益于上述基体结构,C_(f)/C-ZrC-SiC复合材料的弯曲强度和模量分别达到323.2 MPa和46.6 GPa,表现为韧性断裂。采用氧乙炔实验进行抗烧蚀测试,在表面温度为1800~1900℃下,ZrC含量较多的C_(f)/C-ZrC-SiC复合材料质量烧蚀率和线烧蚀率分别为1.263 mg/s和2.367μm/s,ZrC含量较少的C_(f)/C-SiC-ZrC复合材料分别为2.056 mg/s和5.067μm/s,C_(f)/C-ZrC-SiC复合材料表现出更加优异的抗烧蚀性能。
C_(f)/C-ZrC-SiC composites were fabricated via reactive melt infiltration(RMI)with stitched carbon fiber preform and Si-Zr alloy as reactants.The microstructure of C_(f)/C-ZrC-SiC composites was analyzed by SEMEDS and XRD.It can be concluded that SiC-ZrC ceramic matrix has uniform distribution in the C_(f)/C-ZrC-SiC composites.Benefiting from the above matrix microstructure,the bending strength and modulus of C_(f)/C-ZrC-SiC composites can reach up to 323.2 MPa and 46.6 GPa,respectively.The mass ablation rate and linear ablation rate of C_(f)/C-ZrC-SiC composites with high ZrC content are 1.263 mg/s and 2.367μm/s,respectively;and 2.056μm/s and 5.067 mg/s for C_(f)/C-SiC-ZrC composites with less ZrC content,respectively.C_(f)/C-ZrC-SiC composites show good ablation resistance.
作者
杨良伟
陈昊然
金鑫
刘伟
刘俊鹏
YANG Liangwei;CHEN Haoran;JIN Xin;LIU Wei;LIU Junpeng(Research Institute of Aerospace Special Materials and Processing Technology,Beijing 100074)
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2023年第4期43-47,共5页
Aerospace Materials & Technology
基金
国家自然科学基金资助(21803062)。
