摘要
基于正弦函数型式的交变温度模型,开展了固体火箭发动机的传热分析,研究了药柱温度的时滞与分布规律;针对大长径比药柱的温度规律,基于有限元分析结果构造了等效温度算法。结果表明,大长径比药柱温度的空间分布、时滞性均与径向位置相关,轴向差异不明显;等效温度可近似由肉厚中部偏外侧(约0.58倍肉厚处)的特征点表征,其误差在2℃以内,滞后时间不超过5 min。
Based on sinusoidal ambient temperature, the time-lag and spatial distribution of temperature responses were ana- lyzed. Arithmetic for equivalent temperature was formulated, for the usage on grain with greater L/R.It indicates that both time-lag and spatial distribution of temperature depend on radial location, and equivalent temperature approximates a feature point＇s response with the absolute difference of 2℃ as well as the maximal lag-time of 5 min.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第6期818-820,826,共4页
Journal of Solid Rocket Technology
关键词
药柱
交变环境
温度时滞
等效温度
grain
alternating surroundings
time-lag of temperature
equivalent temperature
