C/SiC复合材料的烧蚀机理试验研究  

Experimental Research on Ablation Mechanical of C/SiC Composites

作　　者：付斌 王永海 陈鑫 曹占伟 阎君[3] FU Bin;WANG Yonghai;CHEN Xin;CAO Zhanwei;YAN Jun(Science and Technology on Space Physics Laboratory,Beijing,100076;School of Energy and Power Engineering,Xi'an Jiaotong University,Xi'an,710049;China Academy of Launch Vehicle Technology,Beijing,100076)

机构地区：[1]空间物理重点实验室,北京100076 [2]西安交通大学,能源与动力工程学院,西安710049 [3]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术（中英文）》2024年第4期77-80,共4页Missiles and Space Vehicles

基　　金：国家自然科学基金(No.12102056)。

摘　　要：C/SiC复合材料具有优异的热力学性能,在临近空间领域具有较好的应用前景。针对C/SiC复合材料的烧蚀机理理论方法开展研究,建立了C/SiC复合材料主/被动氧化烧蚀分析方法,并在传统主动和被动氧化烧蚀的基础上,对于更高温度条件则采用一种升华分解烧蚀模型。通过设计典型状态电弧风洞试验,验证了主/被动氧化模型烧蚀、升华分解烧蚀模型的准确性,试验结果表明典型状态下C/SiC复合材料无因次质量烧蚀率与理论值吻合,有关研究及结果可以为C/SiC复合材料防热设计分析提供参考。C/SiC composite material for hypersonic vehicle structure has a broad application in near-space area.The active/passive ablation performance of the C/SiC composite is studied numerically.An approach for active sublimation ablation performance up the 2000℃of C/SiC composite materials is proposed and some wind tunnel experiments have been designed and completed.The results show that the ablation performance proposed has good accuracy compared with the wind tunnel results.The results can provide a reference for the structure and thermal protection design and safety assessment of the hypersonic vehicles based on C/SiC composite material.

关 键 词：C/SIC复合材料 烧蚀机理 升华分解 防热设计 氧化烧蚀 

分 类 号：TB332[一般工业技术—材料科学与工程] V42[航空宇航科学与技术—飞行器设计]