再入飞行器热化学非平衡流场磁流体动力学控制机理  

Mechanism analysis of thermochemical nonequilibrium flow field for re-entry vehicle with magnetohydrodynamic control technology

作　　者：罗仕超 胡守超[1,2] 柳军[3] 吴里银 孔小平 常雨[1,2] 吕明磊 LUO Shi-Chao;HU Shou-Chao;LIU Jun;WU Li-Yin;KONG Xiao-Ping;CHANG Yu;LV Ming-Lei(Hypervelocity Aerodymamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Laboratory of Aerodynamics in Multiple Flow Regimes,Mianyang 621000,China;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000 [2]中国空气动力研究与发展中心跨流域空气动力学重点实验室,绵阳621000 [3]国防科技大学,空天科学学院,长沙410073

出　　处：《中国科学：物理学、力学、天文学》2024年第7期185-196,共12页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家重点研发计划(编号:2019YFA0405300,2019YFA0405200)资助项目。

摘　　要：理论研究基础上建立热化学非平衡流场、外加磁场及霍尔电场耦合计算方法,数值分析不同外加磁场条件下典型再入飞行器高温热化学非平衡流场控制效果.研究表明,区别于量热完全气体,考虑高温气体效应后,化学反应吸热,流场温度降低,降低高超声速磁控热防护效率;高焓热电离磁流体绕流流场,驻点区域逆流向的洛伦兹力分量对流体的减速,而肩部区域法向洛伦兹力改变局部流场结构,使得激波发生偏折;磁控热防护系统绝缘壁面情况下霍尔效应对磁控效果影响较小,肩部区域甚至有助于增强防热效果.绝缘壁面条件下,典型状态的驻点热流和肩部热流分别降低26.5%和52.7%,热流控制效果优于导电壁面.Based on theoretical research,a coupled calculation method is established for the thermochemical nonequilibrium flow field,external magnetic field,and Hall electric field.Subsequently,the effect of controlling the high-temperature thermochemical nonequilibrium flow field of a typical re-entry vehicle is numerically analyzed under different conditions of applied magnetic fields.The results show that,unlike perfect gases,considering the effect of high-temperature gas,the chemical reaction absorbs heat and decreases the flow-field temperature,reducing the efficiency of the hypersonic magnetohydrodynamic(MHD)thermal protection system.In the high-enthalpy thermally ionized MHD flow field,the counterflow Lorentz force in the stagnation-point region decelerates the fluid,while the normal Lorentz force in the shoulder region alters the structure of the local flow field,deflecting shock waves.The influence of the Hall effect on the flow field could be negligible when using insulation walls.Under such conditions,the stagnation-point and shoulder heat flux in typical states are reduced by 26.5% and 52.7%,respectively,and the control effect of the heat flux is better than using conductive walls.

关 键 词：再入飞行器 热化学非平衡 磁流体动力学 流动控制 数值模拟 

分 类 号：V419[航空宇航科学与技术—航空宇航推进理论与工程]