摘要
为了降低成本和简化工艺,以SiC-ZrC复相陶瓷单源先驱体(聚锆碳硅烷,PZCS)作为原材料,通过先驱体浸渍-裂解(PIP)工艺成功制备得到C/C-SiC-ZrC复合材料。PZCS先驱体的裂解行为采用TG分析表征,高温裂解产物的相组成、微观形貌及元素分布等通过XRD、SEM及EDS表征。结果表明,PZCS先驱体能够得到ZrC、SiC均匀分散的均相SiC-ZrC复相陶瓷,其1000℃陶瓷产率为53.82%,可作为PIP工艺制备复合材料的新型先驱体材料。C/C-SiC-ZrC复合材料的弯曲强度达271MPa,断口形貌观察发现,大量纤维呈拔出状态,复合材料表现出准弹性破坏行为。
For cost reduction and simplying the process,a single-source precursor(polyzirconocenecarbosilane,PZCS)for silicon carbide and zirconnium carbide multi-phase ceramic(SiC-ZrC)was successfully used to fabricate C/C-SiC-ZrC composites by polymer infiltration and pyrolysis process(PIP).The pyrolysis process of PZCS precursor were analyzed by thermogravimetry(TG).The phase composition,microstructure and element distribution of the pyrolyzed samples at high temperature was characterized by X-ray diffraction(XRD),scanning electron microscope(SEM)and energy dispersive spectrometer(EDS).The obtained results demonstrated that PZCS showed high ceramic yields(up to 53.82%at the temperature of 1000℃)with formation of homogeneous SiC-ZrC multi-phase ceramics,which was considered as a novel polymeric precursor.The flexural strength of C/C-SiC-ZrC composites was 271MPa.There were a large number of carbon fiber bundles pull-out,and the composites exhibited a pseudo-plastic fracture behavior.
作者
朱世步
刘津生
闫联生
张少飞
孟祥利
崔红
Zhu Shibu;Liu Jinsheng;Yan Liansheng;Zhang Shaofei;Meng Xiangli;Cui Hong(Xi’an Aerospace Composite Research Institute,Xi’an 710025)
出处
《航天制造技术》
2021年第1期23-28,共6页
Aerospace Manufacturing Technology
基金
国防基础科研项目(JCKY2017203C041)。
