2D C_f/SiC-Cu复合材料的制备和性能  

2D C_f/SiC-Cu composites fabricated by precursor pyrolysis

作　　者：简科[1] 陈朝辉[1] 胡海峰[1] 王其坤[1] 马青松[1] 

机构地区：[1]国防科技大学航天与材料工程学院国防科技重点实验室,长沙410073

出　　处：《中国有色金属学报》2005年第12期1933-1937,共5页The Chinese Journal of Nonferrous Metals

基　　金：国防预研基金资助项目(51488030105ZS9504)

摘　　要：针对固体火箭发动机喉衬的使用工况,提出并采用先驱体转化法制备了一种新型的复合材料,2D Cf/SiC-Cu材料(其中Cu作为发汗剂),对其力学性能和烧蚀性能进行了考察。结果表明:采用先驱体转化法可以制备出力学性能较好的2D Cf/SiC-Cu材料,弯曲强度、剪切强度和断裂韧性分别达到263 MPa,27.7 MPa和15.7MPa.m1/2。材料密度为2.24 g/cm3,在氧乙炔焰中烧蚀60 s后,材料结构保持完整,力学性能仍能满足喉衬材料的使用要求,质量损失为0.124 g。因此,2D Cf/SiC-Cu材料具有较低的密度、良好的力学性能和较好的抗烧蚀性能,是一种有希望的固体火箭发动机喉衬备选材料。Based on the working environments of the solid rocket nozzle throat, a proposal to improve anti-ablative property of 2D C/SiC composites by introduction of Cu into C/SiC composites and decreasement of surface temperature through Cu transpiration was presented. 2D C/SiC-Cu composites were prepared by precursor infiltration and pyrolysis. The mechanical properties and ablative properties were investigated. The flexural strength, shear strength and fracture toughness of the 2D Cf/SiC-Cu composites reach 263 MPa, 27.7 MPa and 15.7 MPa · m^1/2 , respectively. The desity of the samples is 2.24 g/cm^3 , and the samples mass loss is 0. 124 g when exposed for 60 s in a flowing oxyacetylene torch environment. The mechanical properties of 2D Cf/SiC-Cu composites could still satisfy the requirements of the solid rocket nozzle throat. Compared to other throat materials, 2D Cf/SiC-Cu composites has lower density and better ablative properties.

关 键 词：2D Cf/SiC-Cu材料 先驱体转化 烧蚀性能 力学性能 

分 类 号：TB323[一般工业技术—材料科学与工程]