高超声速飞行器逆向射流减阻防热技术综述  

Review of Opposing Jet Drag Reduction and Thermal Protection Technology for Hypersonic Vehicle

作　　者：高广宇 刘冰[1] 黄伟[1] 冀晨 钮耀斌 Gao Guangyu;Liu Bing;Huang Wei;Ji Chen;Niu Yaobin(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《战术导弹技术》2021年第4期67-75,共9页Tactical Missile Technology

基　　金：国家自然科学基金项目(11972368、11802340)。

摘　　要：高超声速飞行器在飞行中存在高阻力和气动加热两大问题,逆向射流作为一种有效的减阻防热技术近年来得到广泛研究。基于逆向射流流场结构,介绍了逆向射流减阻防热方案的结构特征,论述了逆向射流减阻防热机理。通过与其它减阻防热方案进行对比,分析了逆向射流减阻防热方案存在的优势与不足。重点综述了逆向射流作为高超声速飞行器减阻防热方案的发展历史和研究现状,介绍了四种逆向射流与其他流动控制技术的组合方案。最后进一步探究了该技术未来发展趋势。High resistance and aerodynamic heating are two major problems in the flight of hypersonic vehicle.The opposing jet as an effective drag reduction and thermal protection technology has been widely studied in recent years.Based on the flow field structure of opposing jet,the structural characteristics and mechanism of the opposing jet drag reduction and thermal protection scheme are introduced.By comparing with other drag reduction and thermal protection schemes,the advantages and disadvantages of the opposing jet drag reduction and thermal protection scheme are analyzed.The development history and research status of opposing jet as the drag reduction and thermal protection scheme of hypersonic vehicle are reviewed,and four combined schemes of opposing jet with other flow control technologies are introduced.Finally,the future development trend of this technology is further explored.

关 键 词：逆向射流 减阻 防热 高超声速 减阻杆 迎风凹腔 发汗冷却 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]