C/C复合材料预制体的研究进展

Research Progress on Preforms of C/C Composites

C/C复合材料是航空航天领域重要的热结构材料,碳纤维预制体是其最主要的基础技术之一,决定着C/C复合材料的各项性能。本文主要介绍了针刺毡、细编穿刺预制体和轴棒编织预制体等C/C预制体,对比了不同预制体的工艺方法、性能和应用特点。针刺毡预制体由于成本低、烧蚀均匀等特点,广泛应用在固体火箭发动机喷管和飞机刹车盘领域;细编穿刺预制体具有纤维体积含量高、致密化周期短和烧蚀率低等特点,应用在固体火箭发动机喉衬;轴棒编织预制体由于织物中70%以上纤维垂直于燃气流方向,提高了材料的抗烧蚀性能,适于制造大型固体火箭发动机。针对国内预制体的研究状况,提出了要加强预制体的孔隙结构、纤维排布等对C/C复合材料的力学、热物理学以及后续致密化工艺影响的研究,更好地促进预制体的发展,进一步提升我国C/C复合材料的性能。

Carbon/carbon(C/C)composites are important fundamental thermal-structure materials in aeronautic and astronautic fields.One of the most primary basic technologies of C/C composites is the manufacture of carbon fiber preforms which determines the performances of C/C composites.In this paper,the preforms including needle-punched felt,fine weave pierced and axial carbon rod weave fabric are introduced,and the process,properties and applications of those preforms are compared.Due to the low cost and homogeneous ablation,needle-punched felt preforms are extensively used in solid rocket motor nozzle and aircraft brake disc.Fine weave pierced preforms are applied in SRM because of high fiber volume content,short densification cycle and low ablative rate.With the excellent ablative rate attributed to more than 70%fiber perpendicular to the gas flow direction,axial carbon rod weave fabric is used in large SRM.For the domestic research status of preforms,it is suggested that the research involving the effect of pore structure and fiber distribution on mechanical,thermal physics properties and the subsequent densification of C/C composites should be further enhanced in order to promote the performance of C/C composite material