轴编C/C复合材料喉衬的多尺度烧蚀分析方法  

Multiscale approach to ablation modeling of in-plain C/C composite for nozzle throat

作　　者：汪海滨[1] 李鑫[1] 

机构地区：[1]中国航天科技集团公司四院四十一所固体火箭发动机燃烧热结构与内流场国防科技重点实验室,西安710025

出　　处：《固体火箭技术》2017年第3期295-301,共7页Journal of Solid Rocket Technology

摘　　要：针对轴编C/C复合材料的结构形式和烧蚀机理,建立了喷管喉衬烧蚀的多尺度分析方法。通过宏观-微观的渐进分析,获得了喷管喉衬的烧蚀率和烧蚀形貌。数值模型反映了喷管热反应边界均匀反应、流场参数、燃气传质过程和材料微观烧蚀对喉衬烧蚀性能的影响。数值计算结果和实验数据吻合较好,表明所建立的数值模型可有效预测轴编C/C复合材料喉衬的烧蚀性能。A multiscale approach is used to model and analyze the ablation of porous materials.Models are developed for the e- rosion of a carbon performs based on the microstructure of in-plane C/C composite. Microscopic and macroscopic approaches are ap- plied with progressive degrees of complexity to gain a comprehensive understanding of the ablation process. The numerical model considers the solution of heterogeneous chemical reactions at the nozzle surface, transport parameters and thermodynamic properties, heat conductivity of the materials, gas diffusion of the materials and mass losses modeled at a microscopic scale.The calculated re- sults show an excellent agreement with the experimental data, and the simulation method has been proved to be effective to predict the erosion of C/C composite.

关 键 词：轴编C/C复合材料 多尺度分析方法 数值模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]