摘要
以炭毡作为纤维增强体,采用化学气相渗透工艺研制出低密度的C/C复合材料,进而以低密度炭/炭复合材料为预制体,采用聚碳硅烷和有机锆前驱体作为复相陶瓷前驱体,采用先驱体浸渍裂解工艺成功制备出ZrC/SiC多组元改性C/C复合材料试样。借助万能电子试验机和扫描电镜进行材料的力学性能和微观结构分析。结果表明:包含ZrC颗粒的SiC相双组元弥散分布在C/C复合材料基体中,且随着前驱体中有机锆含量的增加,力学性能出现先升后降的趋势,当有机锆前驱体质量分数为25%时,改性C/C复合材料弯曲强度和弯曲模量较优,分别为240.61MPa和17.25GPa。
Carbon-carbon composites of low density were prepared by chemical vapor infiltration process (CVI) using carbon felt as fi- ber reinforcement. ZrC/ SiC modified C/C composites were fabricated through precursor infiltration and pyrolysis process (PIP) using a hybrid precursor including polycarbosilane and organic zirconium-contained polymeric precursor as impregnant on the basis of C/C of low density. Mechanical properties and microstructural analysis were performed by Z100 universal electron test equipment and scanning electron microscope respectively. The results show that the silicon carbide phase including zirconium carbide particle dispersed symmet- rical in the matrix of C/C composites, meanwhile the mechanical properties ascend earlier and descend later as the content of organic zirconium-contained polymeric precursor increased. The flexual properties and modulus maximum are 241MPa and 17.25GPa separate- ly when the ratio of organic zirconium polymeric precursor is 25%.
出处
《航空材料学报》
EI
CAS
CSCD
北大核心
2014年第3期69-73,共5页
Journal of Aeronautical Materials