摘要
对高温热冲击下固体火箭发动机的温度场分布进行了研究。基于固体火箭发动机在高温热冲击下的简化分析模型和控制方程,提出了一种求解连续层合结构热传导的分离变量法,获得了高温热冲击下固体火箭发动机层合结构温度场的解析解。
The temperature field distribution in solid rocket motor with high-temperature thermal shock was studied in this paper. A variable-separating method was proposed for solving laminated structures heat conduction problem based on simplified analysis model of solid rocket motor with high-temperature thermal shock. The analytical solution of the temperature field of solid rocket motor laminated structures was obtained.
出处
《上海航天》
2009年第3期26-29,61,共5页
Aerospace Shanghai
基金
国防科大预研基金资助项目(JC06-01-01)
关键词
固体火箭发动机
温度场
有限元法
分离变量法
连续层合结构
Solid rocket motor
Temperature field
Finite element method
Variable-separating method
Laminated structure
