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针对高超音速飞行器、可重复使用运载器和下一代火箭发动机等超高温使用环境的工况要求,提出在2D C/SiC复合材料体系中引入耐超高温相ZrB2。采用先驱体转化法制备了不同ZrB2含量的2D C/SiC-ZrB2新型复合材料,考察了ZrB2含量对材料力学性能、微观结构和抗烧蚀性能的影响。结果表明,材料的力学性能(弯曲强度和弯曲模量)随着材料中ZrB2含量的增加有一定的下降,材料的抗烧蚀性能明显提高。其中含ZrB2体积分数为19.4%的试样弯曲强度达到242.6 MPa,弯曲模量为37.1 GPa;经氧乙炔焰烧蚀考核90 s后,试样表面温度达到2329℃,线烧蚀率为0.015 mm/s,质量烧蚀率为0.005 g/s。
In order to meet the operating conditions of hypersonic vehicles, such as hypersonic vehicles, reusable vehicles and next generation rocket engines, the authors propose to introduce ZrB2 into the 2D C / SiC composites system. New 2D C / SiC-ZrB2 composites with different content of ZrB2 were prepared by the precursor transformation method. The effects of ZrB2 content on the mechanical properties, microstructure and ablation resistance of the composites were investigated. The results show that the mechanical properties (bending strength and flexural modulus) of the material decrease with the increase of ZrB2 content in the material, and the ablation resistance of the material is obviously improved. The flexural strength of the specimen with ZrB2 volume fraction of 19.4% was 242.6 MPa and the flexural modulus was 37.1 GPa. After 90 s of oxyacetylene flame ablation test, the surface temperature of the sample reached 2329 ℃ and the ablation rate was 0.015 mm / s, mass ablation rate of 0.005 g / s.