%0 Journal Article
%T 稀薄流高超声速飞行器气动加热耦合计算
%A 屈程
%A 王江峰&lt
%A /br&gt
%A QU Cheng
%A WANG Jiangfeng
%J 国防科技大学学报
%D 2016
%R 10.11887/j.cn.201605018
%X 针对稀薄流域高超声速飞行器的气动加热问题，开展耦合数值计算研究。通过引入牛顿冷却定律，将直接模拟蒙特卡洛数值模拟方法与结构传热计算方法相结合，设计一种可对全机外形进行气动热和结构传热计算的高效松耦合方法，实现飞行器防热层结构材料温度分布特性的数值模拟。在以钝锥外形为例对直接模拟蒙特卡洛数值模拟程序进行验证的基础上，采用该方法对X37B轨道飞行器外形长时加热与结构传热过程进行数值模拟，给出结构温度及热流密度随飞行时间的变化规律。研究结果表明，设计的耦合计算方法能够模拟稀薄流域高超声速飞行器的气动加热及结构传热耦合过程，可为该类飞行器的气动热分析及热防护设计提供技术支持。</br>A coupling method was presented to deal with the heating problems of hypersonic vehicles in rarefied flow. The DSMC (direct simulation Monte Carlo) method was combined with the heat conduction equation by introducing the Newton cooling law. An efficient loose coupling procedure which can calculate the aerodynamic heat and structure heating of vehicle configuration was designed to simulate the temperature distribution of thermal protection systems. After taking the blunted cone as an example to validate the DSMC code, a numerical experiment was conducted to simulate the structure temperature and heat flux distribution characteristics of the X37B orbital vehicle shape in cruise state. The results show that the presented coupling method can simulate the aerodynamic heating process of a hypersonic vehicle in rarefied flow, and can provide technical support for the design of rarefied-flow hypersonic vehicles in terms of thermal protection systems and aerodynamic heating characteristics analysis.
%K 稀薄流 高超声速 气动热 结构传热 牛顿冷却定律 直接模拟蒙特卡洛 松耦合&lt
%K /br&gt
%K rarefied flow hypersonic aerodynamic heat structure heating Newton cooling law direct simulation Monte Carlo loose coupling
%U http://journal.nudt.edu.cn/gfkjdxxb/ch/reader/view_abstract.aspx?file_no=201605018&flag=1