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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。
Aiming at the problem of aerodynamic heating of hypersonic aircraft in leveled watershed, a coupled numerical calculation is carried out. By introducing the Newton’s cooling law, the direct simulation Monte Carlo numerical simulation method is combined with the heat transfer calculation method to design an efficient and loosely coupled method that can calculate the thermal profile and heat transfer of the whole machine profile, Numerical Simulation of Temperature Distribution in Layered Materials. Based on the example of the blunt cone shape, the numerical simulation program of direct simulation Monte Carlo is verified. The method is used to simulate the long-term heating and the structure heat transfer of the X37B orbiter. The temperature and heat flux density Flight time changes. The results show that the designed coupling calculation method can simulate aerodynamic heating and heat transfer coupling of hypersonic aircraft in lean watershed, and provide technical support for the aerodynamic analysis and thermal protection design of such aircraft.