摘要
采用碳纤维双股双向穿刺预制体,通过预制体定型、高温热处理、CVI致密化和热等静压增密等工序制备了密度大于1.9g/cm-3的高超飞行器热防护组件用C/C复合材料,对制备的高密度C/C复合材料进行力学性能研究,实验结果表明,XY向拉伸强度为131 MPa,Z向拉伸强度为126 MPa,XY向压缩强度为168 MPa,Z向压缩强度为195MPa,XY向弯曲强度为175 MPa,剪切强度为36 MPa。
A C/C composite material for thermal protection components of hypersonic aircraft with a density greater than 1.9g/cm3 was prepared using carbon fiber double stranded bidirectional puncture preforms through preform shaping,high-temperature heat treatment,CVI densification,and hot isostatic pressing densification processes.The mechanical properties of the prepared high-density C/C composite material were studied.The experimental results showed that the XY tensile strength was 131 MPa,the Z-tensile strength was 126 MPa,the XY compressive strength was 168 MPa,the Z-compressive strength was 195 MPa,the XY bending strength was 175 MPa,and the shear strength was 36 MPa.
作者
李刚
魏程
魏喜龙
于柏峰
田忠恩
李思博
侯传礼
LI Gang;WEI Cheng;WEI Xilong;YU Baifeng;TIAN Zhongen;LI Sibo;HOU Chuanli(Harbin FRP Institute Co.,Ltd.,Harbin 150028,China)
出处
《中国建材科技》
2025年第S1期199-202,共4页
China Building Materials Science & Technology
基金
中国建材集团关键核心技术攻关“揭榜挂帅”项目(编号:2023SJYL01)。
关键词
细编穿刺预制体
C/C复合材料
力学性能
fine woven puncture prefabricated body
C/C composite materials
mechanical property
