近程高速弹头的温度场与热应力数值仿真研究

采用工程估算方法,计算了近程高速弹头的非定常气动加热。利用气动加热以及蒙皮内部热传导建立热流量方程,得到沿弹体的温度-时间分布。基于特定的飞行条件,得出瞬时温度场的分布,以此作为有限元瞬态热分析温度边界条件。在有无沿厚度方向的温度梯度下,进行了热应力分析。计算结果表明,本方法快速、简捷,可应用于近程高速导弹的概念研究和多目标优化设计。

Research of Numerical Simulation Method in Temperature and Thermal Stress of Short Range High Speed Missile

Using engineering estimating method,one stead aerodynamic heating of high speed missile was calculated.Adopting aerodynamic and interior heat transfer of wall missile,heat flux equation was made,and then the temperature-time distribution of along missile was obtained.Based on the special flight condition,the distribution transient temperature field was obtained,as the temperature boundary condition of transient thermal analysis.At the temperature gradient along thickness or not,thermal stress was calculated. Result shows that this method is fast and effective,and applies in concept research and multiple objective design of high speed of short range missile.