摘要
首次采用共熔法制备超高温陶瓷基复合材料,三个样品初始组分分别为ZrB_2与鳞片石墨,ZrB_2、TaB_2、SiC及鳞片石墨,ZrB_2、MoSi_2与鳞片石墨。研究结果表明,共熔法制备的复合材料中各相分散均匀,产物中的石墨高度有序,石墨层间距分别为0.335 4、0.335 9与0.337 7 nm,且三者的微晶厚度分别为63.4、51.5及68.7 nm,拉曼光谱结果表明硼已经掺杂进入了石墨的网格结构。所制得的超高温陶瓷基复合材料样品中均存在一定的孔隙率,且制备的超高温陶瓷基复合材料的热导率较低。该方法为一种新型、快速、一步法制备超高温陶瓷基复合材料工艺。
Ultra-high temperature ceramic matrix composites were firstly made by eutectic method. The composites were made from ZrB_2 and flake graphite,ZrB_2,TaB_2,SiC and flake graphite,or ZrB_2,MoSi_2 and flake graphite,respectively. Results shows that different phases distribute uniformly in these composites,and the graphite phases in the composites were highly ordered. The d002 values of the graphite in the composites were 0.335 4,0.335 9 and 0.3377 nm,and the Lcvalues were 63.4,51.5 and 68.7 nm,respectively. Boron had already doped into the carbon net,as indicated by the Raman analysis,and some amount of pores existed in the composites. Also,thermal conductivity coefficient of the composites were not very high. Eutectic method could be a promising method for making ultra-high temperature ceramic matrix composites.
作者
杨金华
刘占军
郭全贵
YANG Jinhua;LIU Zhanjun;GUO Quangui(Aviation Key Laboratory of Science and Technology on Advanced Corrosion and Protection for Aviation Materials, AECC Beijing Institute of Aeronautical Materials, Beijing 100095;National Key Laboratory of Advanced Composites, AECC Beijing Institute of Aeronautical Materials, Beijing 100095;Key Laboratory of Carbon Materials, Institute of Coal Chemistry, Chinese Academy of Sciences, Taiyuan 030001)
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2018年第1期37-43,共7页
Aerospace Materials & Technology
