高超声速飞行复现风洞理论与方法
SHOCK TUNNEL THEORY AND METHODS FOR DUPLICATING HYPERSONIC FLIGHT CONDITIONS
查看参考文献17篇
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文摘
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针对高超声速飞行伴随的热化学反应流动,本文回顾了郭永怀先生的科研理念和学科布局,综述了他亲手成立的高温气动团队在高超声速飞行风洞实验模拟理论与方法方面的研究进展.高温气体的迅速产生与迅速应用是一种理想的风洞运行方法,而激波管就是这样一种实验装备.论文首先介绍了激波管技术的基本理论与方程,指出将其用于高超声速流动实验模拟时所具有的独特优势.然后讨论了应用激波风洞复现需要的高超声速飞行状态的可行性、基本方程和需要解决的关键问题.针对这些关键问题,进一步介绍了如何应用爆轰现象研发激波风洞驱动技术的理论,并给出了基于爆轰驱动方法的技术发展和工程应用验证.最后,论文介绍了爆轰驱动激波风洞的界面匹配条件,该条件奠定了长实验时间激波风洞运行基础,是其他驱动方法尝试解决而没能完全解决的难题.高温气动团队关于高超声速飞行复现风洞的理论与技术研究,实现了郭永怀先生的战略规划,成就了国际领先的高超声速热化学反应流动研究平台. |
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其他语种文摘
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This paper reviews the scientific research philosophy and discipline layout of Prof. Yung-huai Kuo in the field of thermo-chemically reacting flows occurring in hypersonic flights, and summarizes the research progress in shock tunnel theories and methods for duplicating hypersonic flight conditions. The work has been achieved from 50 years effort dedicated by the High Temperature Gas Dynamics Research Team founded by Prof. Kuo. Rapid generation and rapid application of high temperature gas are an ideal method for wind tunnel operation, and a shock tunnel is such an experimental facility. The fundamental theory and governing equations for shock tunnel are presented first, and these demonstrate the unique advantages of shock tunnel technology for the ground-based testing of hypersonic vehicles. Then the feasibility, basic equations and key problems in the shock tunnel technology for duplicating required hypersonic flight conditions are discussed. Aiming at solving the key problems, a theory is proposed for the detonation-driven shock tunnel from the technical development of detonation driver and its engineering application/verification. Finally, the tailored condition for the detonation-driven shock tunnel is introduced, and lays the foundation for the operation of shock tunnels with long test time. This condition is one of the most difficult problems encountered in developing high-enthalpy shock tunnels. The problem has been investigated for decades, but not solved perfectly. With the proposed theory and methods, several high-enthalpy tunnels are developed for covering the full flight envelope of hypersonic vehicles and its applications show that the theory proposed here is successful and important for aerodynamic and kinetic study in the hypersonic research field. The Team’s research work on the hypersonic ground testing facilities has realized the strategic goal of Prof. Kuo’s discipline planning, and a world leading research platform was established for exploring hypersonic thermo-chemically reacting flows. |
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来源
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力学学报
,2018,50(6):1283-1291 【核心库】
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DOI
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10.6052/0459-1879-18-238
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关键词
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高超声速
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激波风洞
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复现飞行条件
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爆轰驱动
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缝合条件
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地址
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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
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中国科学院大学工程科学学院宇航工程科学系, 北京, 100049
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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0459-1879 |
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学科
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航空 |
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基金
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国家自然科学基金资助项目
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文献收藏号
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CSCD:6394695
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参考文献 共
17
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