摘要
本文根据炭化烧蚀材料的防热机理,认为防热材料表面化学烧蚀后退、热解膨胀和内部温度升高引起线膨胀是造成防热层厚度变化的因素,国内外学者主要研究了表面化学烧蚀后退对飞行器外形变化和温度场的影响,而对于后两者的具体影响却少有研究。本文数值模拟了高硅氧-酚醛炭化材料的烧蚀热响应过程,分析和解释了计算结果,说明了防热材料的线膨胀和热解膨胀对外形和温度场有较大的影响。
The surface ablation, pyrolysis expansion and linear expansion of thermal protection layer are the key factors for the thickness variation of thermal protection layer and internal temperature field according to the character of charring thermal protection materials. The surface ablation are widely discussed while other two factors are rarely involved. The ablation and internal temperature field for the phenalic-SiO2 thermal protection materials are simulated numerically, and the results indicated that pyrolysis expansion and linear expansion are of important influences for the thickness variation of thermal protection layer and internal temperature field.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2004年第4期631-633,共3页
Journal of Engineering Thermophysics
关键词
烧蚀
炭化
热解膨胀
ablation
charring
pyrolysis expansion
