类航天飞机前身结构与高超声速流场的耦合传热模拟分析

Numerical simulation of fluid-solid-thermal interaction in hypersonic flows

开展了高超声速流场与结构温度场的耦合数值计算.流场部分求解了三维非定常全Navier-Stokes(N-S)方程,空间差分采用Harten-Yee的TVD(总变差衰减)格式,时间离散采用双时间步推进.固体结构传热部分求解了三维非稳态的热传导方程.通过流固交界面,流体从固体部分得到温度边界条件,固体从流体部分得到热流边界条件,从而实现流场和固体温度场的紧耦合计算.用绕无限长圆柱的气动加热计算验证了该算法的有效性,并对类航天飞机前身结构在气动加热过程中的温度变化做了比较详细的分析.计算结果表明,固体结构在遭遇到气动加热后的一段时间内,壁面温升对壁面热流的影响是很大的,由于一体化计算能很好的综合考虑热壁的影响,因此,开展一体化计算是很有必要的.

The unsteady fully Navier-Stokes（N-S） equations were solved by Harten-Yee＇s TVD（total variation diminishing） and dual time march for the flow field.The 3-D unsteady heat conduction equation was solved for the structure.The coupling was processed as follows： the flow field acquired temperature＇s boundary condition from the structure and the temperature field of the structure acquired heat flux＇s boundary condition from flow at the fluid-solid interface.The method proposed here was validated by aerodynamically infinite column.The transformation of head of space shuttle＇s temperature was analyzed in detail during pneumatic heating process.The results show that the increase of wall temperature strongly affects heat flux.Therefore,solid-fluid coupled iteration is very necessary in the simulation since the influence of the increase of wall temperature can be considered.