摘要
以高超声速再入体为例,通过求解Euler方程来确定物面边界层外缘参数。在理论与半经验公式基础上,利用参考焓方法计算了零攻角弹头的表面热流密度,得到了壁面辐射平衡温度曲线,结果验证了高超声速飞行器采用钝前缘的防热效果。在此基础上,利用有限元法,分析了球头驻点区域附近沿厚度方向的温度场,为再入弹头防热方案的初步设计提供了参考。
Taking hypersonic reentry body as an example, the boundary-layer edge parameters are determined by solving Euler equations. The heating flux density of warhead at zero attack angle is calculated by using reference enthalpy method basing on theory and semi-empirical, and the heat proof effect of blunt leading edge is proved by the temperature curve. Based on this, the temperature field along thickness for stagnation region is analyzed by using finite-element method, which provides a reference for heat proof design of the heat protectetion design of reentry body.
出处
《导弹与航天运载技术》
北大核心
2008年第3期41-45,共5页
Missiles and Space Vehicles
基金
高等学校博士学科点专项科研基金(20060217010)资助
关键词
高超声速
弹头
热流密度
温度场
Hypersonic
Warhead
Heating flux density
Temperature field.
