C/SiC陶瓷复合材料推力室的制备与性能表征

Preparation and property characterization of C/SiC composite thruster

采用"化学气相渗透法+聚合物先驱体浸渍裂解法"(CVI+PIP)混合工艺制备出连续炭纤维增强碳化硅陶瓷复合材料(3D C/SiC)推力室,综合考察了复合材料的机械性能、微观结构和气密性能,以及姿控、轨控发动机环境试验考核。结果表明,"CVI+PIP"混合工艺制备C/SiC复合材料不仅工艺周期缩短,而且材料性能优异。复合材料密度达2.1 g/cm3,室温弯曲强度和断裂韧性(KIC)分别达到520 MPa和17.9 MPa.m1/2;而且断裂破坏行为呈现典型的韧性模式。C/SiC复合材料推力室的高温气密性、抗氧化和抗烧蚀性能通过了双燃料液体发动机试验考核。

Continuous carbon fiber reinforced silicon carbide matrix composite thrusters were prepared by using ＂chemical vapor infiltration ＋ precursor impregnation pyrolysis＂ （ CVI ＋ PIP） hybrid process. The mechanical properties, gas tightness and microstructure of 3D C/SiC composites were comprehensively investigated through attitude control and orbit control rocket motor environ-mental test. The results show that CVI ＋ PIP hybrid process can not only shorten process cycle,but also improve composite properties. The density of C/SiC composite can reach 2.1 g/cm^3. The flexural strength and fracture toughness （ KIC） of the composite at room temperature are 520 MPa and 17.9 MPa·m^1/2 respectively. The fracture damage behavior of the composite presents typical toughness mode. High-temperature gas tightness, anti-oxidation and ablation properties of the C/SiC composite thruster are verified through bipropellant liquid rocket motor test.