本文针对轴对称型飞行器前缘部位，采用松耦合方法，开展了二维高超声速流固界面的热耦合计算。满足非稳态N—S方程的外部流场和内部非稳态热传导均采用商用软件FLUENT进行计算。通过对相同时刻，不同松耦合推进时间步长引起的壁面热流密度、壁面温度、表面传热系数的差异对比，得出了松耦合推进时间对以上参数的影响规律，这对有效实施松耦合方法进行高超声速飞行器模拟具有积极意义。
In this article, the loosely-coupled method is applied to simulate a two dimensional hy- personic fluid-solid thermally-coupled flow around the leading edge of an axisymmetric flying vehicle. The outer flow field governed by the unsteady Navier-Stokes equations and the inner temperature field governed controlled by unsteady heat-conduction equation are both solved by the commercial code FLUENT. From the differences of results of heat transfer rate, surface temperature, and heat transfer coefficient which were obtained by the loosely-coupled simulation at the same instant but with different forward time steps for outer and inner computations the influence of forward time steps are revealed. Such results have a positive significance for the research of the hypersonic vehicle flying simulation by the loosely-coupled method.
参考文献
| [1] | Olynick D.;Tam T. .TRAJECTORY-BASED VALIDATION OF THE SHUTTLE HEATING ENVIRONMENT[J].Journal of spacecraft and rockets,1997(2):172-181. |
| [2] | 夏刚,刘新建,程文科,秦子增.钝体高超声速气动加热与结构热传递耦合的数值计算[J].国防科技大学学报,2003(01):35-39. |
| [3] | 黄春生,吴杰,范绪箕.飞行器流场与结构温度场耦合数值分析[J].力学与实践,2004(02):24-26. |
| [4] | 姜志杰,张擘毅,何浩,刘伟强.高超声速飞行器鼻锥的热环境和结构热分析研究[J].导弹与航天运载技术,2009(04):14-17,22. |
| [5] | 杨荣,王强.高超声速旋转体气动加热、辐射换热与结构热传导的耦合数值分析[J].上海航天,2009(04):25-29,64. |
| [6] | S. Rameche Candane;C. Balaji;S. P. Venkateshan .Ablation and Aero-thermodynamic Studies on Thermal Protection Systems of Sharp-Nosed Re-entry Vehicles[J].Journal of heat transfer: Transactions of the ASME,2007(7):912-916. |
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