PIP法制备C/ZrC-SiC复合材料工艺与性能研究  

Process and Properties of C/ZrC-SiC Composites Prepared by Precursor Infiltration and Pyrolysis

作　　者：刘伟 宋环君 于艺 孙同臣[1] 裴雨辰[1] LIU Wei;SONG Huanjun;YU Yi;SUN Tongchen;PEI Yuchen(Research Institute of Aerospace Special Materials and Processing Technology,Beijing 100074)

机构地区：[1]航天特种材料及工艺技术研究所

出　　处：《宇航材料工艺》2019年第4期41-44,共4页Aerospace Materials & Technology

基　　金：国家自然科学基金(21803062)

摘　　要：为了提高超高温陶瓷基复合材料的力学性能和耐烧蚀性能,本文采用前驱体浸渍裂解(PIP)工艺制备了C/ZrC-SiC复合材料,研究了锆硅一体化陶瓷前驱体(ZS)的固化-裂解工艺对C/ZrC-SiC复合材料性能的影响。结果表明:前驱体的裂解温度对复合材料的力学性能影响较大。较高的裂解温度会损坏碳纤维,导致力学性能降低;较低的裂解温度会使碳热还原反应不充分,基体氧含量较高,结构疏松,导致力学性能下降;制备的C/ZrC-SiC复合材料通过了2 850 K的电弧风洞试验考核后线烧蚀率为8.75×10^-4mm/s,呈现出优异的耐烧蚀性能。In order to improve the mechanical properties and ablation resistance of ultra-high temperature ceramic matrix composites,C/ZrC-SiC composites were fabricated by precursor infiltration and pyrolysis(PIP)process.Effects of the pyrolyzing process of zirconium silicon precursor resin on the properties of C/ZrC-SiC composites were investigated.The results showed that the pyrolyzing temperature of ZS precursor resin had great effects on the properties of composites.The mechanical properties decreased at high pyrolyzing temperature due to the damaging of carbon fiber while it also decreased at low pyrolyzing temperature due to high oxygen content.The prepared C/ZrC-SiC composites were tested by 2850 K arc wind tunnel test and the ablation rate was 8.75×10^-4 mm/s,which showed excellent ablation resistance.

关 键 词：前驱体浸渍裂解 C/ZrC-SiC复合材料 固化-裂解工艺 

分 类 号：TB332[一般工业技术—材料科学与工程]