再入飞行器端头烧蚀的耦合计算方法  

Research of Coupling Computational Method about the Nose-Tip Ablation of Reentry Vehicle

作　　者：龙丽平 韩俊 万田[1] 仲峰泉[1,2] 田保未 LONG Li-ping;HAN Jun;WAN Tian;ZHONG Feng-quan;TIAN Bao-wei(Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院力学研究所高温气体动力学国家重点实验室,北京100190 [2]中国科学院大学工程科学学院,北京100049

出　　处：《强度与环境》2021年第2期8-14,共7页Structure & Environment Engineering

基　　金：中国科学院战略性先导科技专项(XDA17030100)。

摘　　要：端头烧蚀是超高速飞行器再入过程中非常关心的问题。端头材料在高温高压环境中,因烧蚀其原有气动外形和结构传热边界不断变化,而气动外形和传热边界的变化又反过来影响端头热流、温度分布和烧蚀量。它们之间表现出复杂的强耦合、非线性特征。本文以碳基材料端头帽烧蚀过程为例,发展了端头帽绕流、烧蚀和结构传热耦合计算方法。通过气动、烧蚀和结构热响应计算程序的耦合和迭代,实现了对端头帽再入烧蚀过程的实时动边界模拟,并在飞行试验条件下,得到了与测量数据基本吻合的结果。Nose-tip ablation is a very important problem in the reentry process of hypersonic vehicle.In the high temperature and high pressure environment,the original aerodynamic shape and structure heat transfer boundary are constantly changing because of the ablation,and the change of aerodynamic shape and heat transfer boundary affects nose-tip heat flux,temperature distribution and ablation quantity in turn.They exhibit complex strong coupling and non-linear characteristics.Taking the ablation process of nose-tip of carbon based materials as an example,the coupling calculation method of flow,ablation and structure heat transfer of nose-tip are developed.Through the coupling and iteration of the calculation program of the aerodynamic,ablation and structure thermal response,the real time moving boundary simulation of the nose-tip reentry ablation process is realized,and the results are basically in agreement with the measured data under the flight test conditions.

关 键 词：再入过程 端头帽 烧蚀 移动边界 多学科耦合计算方法 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]