摘要
国内外高超声速飞行关键技术的验证与考核一直依赖于飞行试验,而高超声速飞行试验费时、昂贵、又具有后验性。所以,为了推动先进空天飞行器的研发,高超声速风洞的理论创新和工程实践一直是一个紧迫的基础性研究课题。本文首先回顾了高超声速风洞研发进展及其存在的问题,讨论了先进空天飞行器地面试验对于风洞技术发展的需求。然后阐述了爆轰驱动激波风洞理论及其技术体系,包括两种核心爆轰驱动方法。中国爆轰驱动高超声速高焓激波风洞(简称中国高超风洞)的研发成功使得高超声速风洞实验实现了从“流动状态模拟”到“飞行条件复现”的跨越,引领了国际高超声速风洞技术的发展。最后本文简述了应用中国高超风洞开展的学科前沿问题研究进展,介绍了由此揭示的高超声速流动的气动力/热规律、真实气体效应影响、高温边界层发展和驻定斜爆轰稳定性的物理机制。这些前沿学科问题源于飞行技术创新和工程应用实践,展示了中国高超风洞研发的必要性和重要性,同时也促进了高超声速飞行关键技术的验证、提升和创新。
The verification and assessment of hypersonic technology has relied on flight tests for decades.However,hypersonic flight tests are time-consuming,expensive,and has a feature of post verification,therefore,the development of hypersonic wind tunnels has become an urgent need to promote the hypersonic research.First,this paper reviews the progress of hypersonic wind tunnels and its existing problems,and discusses the requirements of hypersonic technology for ground testing.Then,the paper expounds the theory and technical system of detonation-driven hypervelocity high-enthalpy shock tunnels,including both the backward and forward detonation drivers.The successful development of the detonation-driven hypersonic high-enthalpy shock tunnels in China(hereinafter referred to as Chinese hypervelocity wind tunnels)have enabled the verification and qualification of the key technology of hypersonic vehicles to achieve a leap from“flow simulation”to“flight duplication”,leading the research of international hypersonic ground testing facilities.Finally,the paper briefly describes the research progress of discipline frontier problems carried out with Chinese hypervelocity wind tunnels,including studies on the aerodynamic force/heating,real gas effects,high-temperature boundary layer development and standing oblique shock instability in hypersonic flows.These fundamental issues originate from technology innovation and engineering practice,demonstrating the necessity and importance of Chinese hypervelocity wind tunnels,while also promoting the verification,improvement and innovation of hypersonic technology.
作者
姜宗林
Jiang Zonglin(State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China)
基金
国家自然科学基金项目(11727901,11532014,12072353)。
关键词
中国高超风洞
正向爆轰驱动技术
真实气体效应
高温边界层
Chinese hypervelocity wind tunnel
forward detonation driver
real gas effect
high-temperature boundary layer
