高超声速流场与结构温度场一体化计算方法

发布时间：2018-01-20 22:03

本文关键词： 流场与结构温度场一体化气动加热有限体积法一体化算法高超声速　出处：《航空动力学报》2016年01期 　论文类型：期刊论文

【摘要】：在对国内外流场与结构温度场一体化计算方法的不足进行细致讨论的基础上,提出了一种高超声速流场与结构温度场一体化计算方法.采用统一的积分方程组作为气动加热和结构传热物理过程的控制方程,对整个物理场进行统一的迎风格式有限体积方法离散,给出了流场与结构交界面上温度、温度梯度及导热系数等参数的计算方法.在时间推进方面,定常状态采用多步龙格库塔迭代格式,非定常状态则采用双时间步长方法.采用发展的一体化算法对二维圆管模型的气动加热和结构传热问题进行了数值模拟.结果表明:2s时驻点物面温度为390K,与其他文献的误差在3.1K范围内;稳定时驻点物面温度为647K.
[Abstract]:On the basis of detailed discussion on the shortage of integrated calculation method of flow field and structure temperature field at home and abroad. In this paper, a hypersonic flow field and structural temperature field are presented. The unified integral equations are used as the governing equations for the physical process of aerodynamic heating and structural heat transfer. The whole physical field is discretized by a unified upwind finite volume method, and the calculation methods of temperature, temperature gradient and thermal conductivity at the interface between the flow field and the structure are given. Multistep Runge-Kutta iterative scheme is used in the steady state. In the unsteady state, the two-time step method is used. The aerodynamic heating and structural heat transfer of the two-dimensional circular tube model are numerically simulated by using the developed integrated algorithm. The results show that:. The surface temperature of the stationary point is 390K at 2s. The error from other literature is within 3.1 K; The stationary point surface temperature is 647K.
【作者单位】：南京航空航天大学航空宇航学院;
【基金】：国家高技术研究发展计划
【分类号】：V211.3
【正文快照】： 随着现代飞行技术的发展,飞行器的飞行速度越来越高,由此引起的气动加热与结构传热问题不可忽视[1-2].传统气动加热/结构传热计算通常采用耦合交替迭代的方法,主要分成以下两个计算过程[3-6]:一为将交界面的物面温度作为流场边界条件计算流场,得到交界边界的热流密度;二为将热

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