摘要
为满足喷管内型面耐烧蚀及背壁绝热的要求 ,以整体炭毡、炭纤维多维编织件等为预制体 ,先进行炭素沉积与石墨化 ,再用 Al2 O3型高温无机胶进行真空 -压力浸渍、烧结 ,制得 C/ Al2 O3功能型复合材料。对增强相炭纤维与陶瓷相 Al2 O3的界面结合强度、无机胶液配方改进、提高烧结温度以及用沥青浸渍 HIP等方面进行了研究。所获得的复合材料外表面导热系数 λ=0 .90 2 W/ (m·K) (80 0℃ ) ,内表面线烧蚀率为 0 .0 1 8mm/ s,电镜照片显示 C/ Al2 O3的界面结合良好。
To meet the requirement of the inner contour erosion resistance and backup insulation for the rocket nozzle, a new functional C/Al 2O 3 carbon ceramic composite was developed by using the inner-heat CVD method. In processing, the whole carbon felt and CF multi-directions woven preforms are, at first, densified with carbon matrix and graphitized, and then impregnated at pressure with Al 2O 3 type inorganic glue, and sintered at 500℃. The experiment investigation was carried out in enhancing the interface strength of carbon and Al 2O 3 glue, improving the Al 2O 3 glue formula to elevating the sintering temperature, and pitch-impregnation and HIP-treatment and so on. Results show that the heat conductivity coefficient of the exterior surface of the C/Al 2O 3 composite material is 0.902W/(m·K)(800℃) and linear erosion rate of its interior surface is 0.018mm/s. The SEM photos show a fine C/Al 2O 3 interface bonding.
出处
《固体火箭技术》
EI
CAS
CSCD
2000年第3期64-69,共6页
Journal of Solid Rocket Technology