摘要
针对高速飞行导弹建立了气动加热及烧蚀的数学计算模型,应用"飞机结构三维温度场分析"程序,根据物体面表面径烧蚀量移动边界,通过"热阻"处理不同结构件的接触问题,成功地进行了烧蚀和温度场的直接耦合求解。计算结果表明了导弹头锥的烧蚀和温度分布规律。
The aerodynamic heating and ablation model of hypersonic projectiles is established. According to ablation quantity moving boundary around structure surfaces as well as by using thermal contact resistance for different structures, directly coupled numerical analysis for ablation and temperature field was done. The program ＂Three-dimensional temperature field analysis in aircraft structure＂ was applied during calculation. Ablation and temperature distribution for the missile toper are shown.
出处
《科学技术与工程》
2009年第18期5425-5427,5431,共4页
Science Technology and Engineering
关键词
温度场
有限元
接触热阻
烧蚀
耦合计算
temperature field finite element model thermal contact resistance ablation coupling calculation
