磁控热防护系统在天地往返运载器上的应用仿真

doi:10.7527/S1000-6893.2020.24501

流体力学与飞行力学

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磁控热防护系统在天地往返运载器上的应用仿真

丁明松, 刘庆宗, 江涛, 董维中, 高铁锁, 傅杨奥骁

中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

收稿日期:2020-07-06 修回日期:2020-07-31 发布日期:2020-09-14
通讯作者: 董维中 E-mail:dongwz1966@163.com
基金资助:
国家重点研发计划（2019YFA0405203）；国家数值风洞工程

Simulation of magnetohydrodynamic heat shield system on reusable launch vehicles

DING Mingsong, LIU Qingzong, JIANG Tao, DONG Weizhong, GAO Tiesuo, FU Yang'aoxiao

Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2020-07-06 Revised:2020-07-31 Published:2020-09-14
Supported by:
National Key Research & Development Plan (2019YFA0405203); National Numerical Windtunnel Project

摘要/Abstract

摘要： 磁控热防护技术在高超声速领域显现出广泛的应用前景。考虑高超声速流动磁流体力学控制涉及的等离子体生成机制、多电离组分导电机理以及电磁流动能量/动量输运机制，通过耦合求解电磁场泊松方程和带电磁源项的高温热化学非平衡流动控制方程组，搭建了高超声速磁控热防护数值模拟平台。结合美国航天飞机"哥伦比亚"号（OV-102）近似外形和5种磁场配置方案，较为系统地开展了磁控热防护系统在高超声速"滑翔返回式"天地往返运载器上的应用仿真研究。结果表明：搭建的磁控热防护仿真平台具备偶极子磁场、均匀磁场、螺线管磁场及多个磁场组合条件下复杂外形飞行器气动热环境数值模拟能力，其校验结果与文献或飞行试验数据符合较好；采用合适的磁场配置能有效降低航天飞机的表面热流，显著改善了航天飞机的气动热环境，典型状态的表面热流下降25%以上；局部磁场方向与流动方向的夹角，在一定程度上决定了洛伦兹力的强度和方向，对磁控效果的影响明显。

关键词: 磁控热防护, 天地往返运载器, 高超声速, 高温气体效应, 气动热

Abstract: Magnetohydrodynamic heat shield technology has a promising future in its application on hypersonic vehicles. Considering the mechanism of plasma formation, conduction of ionization species and transportation of energy and momentum in electromagnetic flow, which are involved in hypersonic magnetohydrodynamic control, we build the numerical simulation platform of the hypersonic magnetohydrodynamic heat shield by solving high temperature nonequilibrium flow governing equations coupled with Poisson’s equation of electromagnetic fields. Using the configuration of American space shuttle "Columbia" (OV-102) and 5 different magnetic field disposition cases, the application simulation of the magnetohydrodynamic heat shield system on the hypersonic reusable launch vehicle is systematically carried out. The results show that the hypersonic magnetohydrodynamic heat shield simulation platform built in this study has the ability to simulate the aerodynamic thermal environment of complex-shaped aircraft in dipole, solenoid, uniform magnetic fields and superposition magnetic fields, and the validation result is in good agreement with the reference or the flight test data; appropriate magnetic field disposition effectively reduces the surface heat flux of the space shuttle and improves the aerodynamic thermal environment, with the surface heat flux under typical condition decreased by more than 25%; the angle between the local magnetic field and the inflow decides the magnitude and direction of Lorentz force to some extent, exhibiting a strong influence on the effect of the magnetohydrodynamic heat shield system.

Key words: magnetohydrodynamic heat shield, reusable launch vehicles, hypersonic, high temperature gas effect, aerodynamic thermal

中图分类号:

丁明松, 刘庆宗, 江涛, 董维中, 高铁锁, 傅杨奥骁. 磁控热防护系统在天地往返运载器上的应用仿真[J]. 航空学报, 2021, 42(7): 124501-124501.

DING Mingsong, LIU Qingzong, JIANG Tao, DONG Weizhong, GAO Tiesuo, FU Yang'aoxiao. Simulation of magnetohydrodynamic heat shield system on reusable launch vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 124501-124501.

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磁控热防护系统在天地往返运载器上的应用仿真

Simulation of magnetohydrodynamic heat shield system on reusable launch vehicles

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