液体火箭发动机喷管延伸段C/C-SiC复合材料的性能  

Performances of C/C-SiC composites for the nozzle extension of liquid rocket engines

作　　者：王坤杰[1,2] 姚冬梅 崔红[1,2] 郑金煌 苏红[1,2] WANG Kunjie;YAO Dongmei;CUI Hong;ZHENG Jinhuang;SU Hong(Xi'an Aerospace Composites Research Institute,Xi'an 710025,China;National and Local Union Engineering Research Center of High-Performance Carbon Fiber Manufacture and Application, Xi'an 710089,China)

机构地区：[1]西安航天复合材料研究所,西安710025 [2]高性能炭纤维制造及应用国家地方联合工程研究中心,西安710089

出　　处：《固体火箭技术》2019年第4期506-512,共7页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(21676163)

摘　　要：采用化学气相渗透(CVI)和液相浸渍裂解(PIP)混合工艺制备出三维针刺C/C-SiC(材料A、B)和C/C(材料C)复合材料,研究了复合材料的力学、抗热震和耐烧蚀等性能以及SiC涂层对烧蚀性能的影响,并采用扫描电子显微镜分析了材料的断裂面和烧蚀面形貌。结果表明,材料A(SiC基体含量较高)的性能较好,其弯曲强度、线烧蚀率及抗热震系数分别达到238.4 MPa、3.0×10^-3mm/s和35.3 kW/m。沉积SiC涂层后,材料A、B和C的线烧蚀率较之前分别降低33.0%、12.5%和37.5%。采用材料A+SiC涂层方案研制的喷管延伸段构件,进行780 s地面热试车考核,试车后构件结构完整。Three-dimensional needle-punched C/C-SiC(composites A and B) and C/C (composite C) composites were prepared by chemical vapor infiltration and liquid impregnation-pyrolysis techniques. The flexural,thermal shock resistance and ablation properties of the composites have been investigated.The effect of SiC coating on the ablation properties of the composites was also analyzed.The fractured and ablation surfaces were checked by scanning electron microscope (SEM).Results showed that the Composite A with higher SiC matrix content has better properties.The flexural strength,linear ablation rate and thermal stress factor reach 238.4 MPa,3.0×10^-3 mm/s and 35.3 kW/m,respectively.Compared to the other uncoated composites, the linear ablation rates of Composites A,B and C with SiC coatings were decreased by 33.3%,12.5% and 37.5%,respectively.The nozzle extension developed by the Composites A and SiC coating scheme was evaluated on the 780 s ground hot-firing test,and the structure of the component was unchanged and maintained integrated after the firing test.

关 键 词：三维针刺 C/C-SIC复合材料 线烧蚀率 热试车 

分 类 号：V258[一般工业技术—材料科学与工程]