摘要
本文针对微型固体火箭中点火阶段的瞬时加热过程,分别采用传统的傅里叶导热模型,C-V模型和双元相滞后（TheDuelPhaseLag）模型,描述了微型固体火箭中的瞬态导热过程,并对微型固体火箭内的温度分布进行了数值模拟。结果表明,在本文所研究的条件下,经历大约40微秒,火药的最高温度大约可上升至180℃,点火的具体过程还与火药的物理化学性质（最小点火能,反应速率等）有关;在升温速率很大时,非傅里叶效应的影响不可以被忽略;Tt和Tq的值越大影响越大。
Three models of thermal conduction (Fourier Model, C-V Model and The Duel Phase Lag Model) are used to describe the transient ignition process in micro rocket. The temperature field in micro rocket was investigated numerically. The results indicated that, under the provided conditions, the maximal temperature in powder may rise to 180癈 at 40 祍, while the details of ignition are correlated to physical chemistry characteristics of powder; if the temperature rising rate is very large, the Non-Fourier effect ca...
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2002年第S1期129-132,共4页
Journal of Engineering Thermophysics
基金
国家重点基础研究发展规划经费资助项目(No.G1999 033106)
关键词
微型固体火箭
点火
非傅里叶导热
micro rocket
ignition
non-Fourier thermal conduction
