摘要
SiC陶瓷复合材料具有抗氧化、耐高温等综合性能,已在宇航领域得到广泛应用,聚合物先驱体——聚碳硅烷经高温裂解,可制备SiC陶瓷复合材料。主要进行了聚碳硅烷的结构与性能分析,以及其用于制备PIP-SiC基陶瓷复合材料的研究。结果表明,C/C-SiC炭陶双基材料结合了C/C复合材料使用温度高、C/SiC复合材料抗氧化性能优良的特点,随着基体中PIP-SiC含量的增加,提高了C/C-SiC复合材料的综合力学性能和抗氧化烧蚀性能。采用"CVI+PIP"工艺研制的3D C/C-SiC复合材料弯曲强度高达468.4MPa,拉伸强度高达348.6 MPa,600 s条件下的氧乙炔烧蚀的线烧蚀率为0.001 7 mm/s、质量烧蚀率为0.000 6 g/s,使C/C-SiC复合材料达到了长寿命的使用目的。
Composites with silicone carbide matrix and coatings have been used widely in aerospace due to its high properties of oxidation protection and thermal endurance.As a kind of polymer precursor, polycarbosilane can be used to prepare silicone carbide matrix composites via polymer pyrolysis in circumstances of high temperature.Structures and properties and PIP-SiC matrix compos ites of polycarhosilane were summarized.Results show that C/C-SiC dual matrix composites combine the features of high operation temperature of C/C and good oxidation resistance of C/SiC composites.The integrated mechanical and ablation resistance properties of C/C-SiC composites are improved with increasing PIP-SiC content.The flexural and the tensile strength of 3D C/C-SiC composites by means of ＂CVI＋PIP＂ process reach 468.4 MPa and 348.6 MPa.The linear and mass ablation rate of oxygen-acetylene under 600 s are 0.001 7 mm/s and 0.000 6 g,/s respectively.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2014年第1期128-133,共6页
Journal of Solid Rocket Technology
