摘要
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。
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.
出处
《系统仿真学报》
EI
CAS
CSCD
北大核心
2008年第5期1170-1173,共4页
Journal of System Simulation
关键词
高超声速
气动加热
工程计算
热应力
导弹
hypersonic
aerodynamic heating
engineering calculation
thermal stress
missile
作者简介
尹莲花（1980-），女，河南人，博士生，研究方向为飞行器热结构分析与优化设计.
刘莉（1964-），教授，博导，研究方向为飞行器设计等.
张帅（1981-），硕士生，研究方向飞行器气动加热与强度分析等。
