摘要
基于对绝热材料烧蚀实验结果的观察和分析,从EPDM绝热材料炭化层微观孔隙结构特征出发,综合考虑多孔结构炭化层内的流动、传热及烧蚀过程,建立了基于炭化层孔隙结构特征的绝热材料热化学烧蚀模型和相应计算方法;对EPDM绝热材料的热化学烧蚀过程开展了数值计算,并将计算得到的质量烧蚀率与烧蚀发动机实验结果进行了比较,结果吻合较好。
An ablation experiment was conducted.On analyzing the micro porous character of charring layer,a thermal-chemical ablation model was established,and a numerical method as well,including the gas flow,species diffusion,gas-solid heat transfer and volumetric thermo-chemical ablation in the porous charring layer,Simulation of the thermo-chemical ablation process of EPDM ablator was carried out and results was compared with experimental data.It shows that the calculated results match well with the experiment data in charring rate,charring layer thickness and ablation mass rate,and the model is valid.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第6期680-683,718,共5页
Journal of Solid Rocket Technology
基金
国家自然科学基金(NSFC50876091)
关键词
绝热层
热化学烧蚀
孔隙结构
数学模型
ablator
thermo-chemical ablation
porosity
mathematical model
作者简介
李强（1976-），男，博士后，主要研究航空宇推进理论与工程。E-mail：leeqiang@nwpu．edu．cn
