激波/湍流边界层干扰中的自适应控制技术  

Adaptive control techniques in the shock wave/turbulence boundary layer interaction

作　　者：黄伟[1] 吴瀚 钟翔宇 杜兆波 柳军[1] HUANG Wei;WU Han;ZHONG Xiangyu;DU Zhaobo;LIU Jun(Hypersonic Technology Laboratory,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学高超声速技术重点实验室,湖南长沙410073

出　　处：《国防科技大学学报》2024年第2期49-61,共13页Journal of National University of Defense Technology

基　　金：国家重点研发计划资助项目(2019YFA0405300);国家自然科学基金资助项目(11972368)。

摘　　要：从激波/湍流边界层干扰机理以及流动控制的迫切需求入手,从自适应涡流发生器、自适应鼓包、自适应微射流以及自适应次流循环四个方面对激波/湍流边界层干扰中的自适应控制技术研究进展进行了总结。分析认为,结合AI技术发展自适应流动控制技术,加速控制方式智能化,可作为新一代高超声速飞行器宽速域飞行的重要技术手段。具体来说,就是通过调节外加激励对高超声速飞行器不同区域实现局部流动加/减速、气动热防护、气动控制等功能,根据流场参数建立控制反馈回路,自适应调整局部流场结构,以满足工程实际需求。Starting from the mechanism of SWTBLI(shock wave/turbulent boundary layer interaction)and the urgent need for flow control,the research progress of the adaptive control techniques in the SWTBLI from four aspects was summarized,namely adaptive vortex generator,adaptive bump,adaptive micro jets and adaptive secondary recirculation jet.Analysis shows that developing adaptive flow control techniques,combined with AI technology,and accelerating intelligent control schemes can be used as an important technical means for wide-speed flight of the new generation hypersonic vehicle.Specifically,it is to realize local flow acceleration/deceleration,aerodynamic thermal protection,aerodynamic control and other functions in different areas of the hypersonic vehicle by adjusting external excitation,and to establish a control feedback loop according to flow field parameters,so it can adaptively adjust the structure of the local flow field to meet the actual needs of engineering.

关 键 词：自适应流动控制 激波/湍流边界层干扰 高超声速飞行器 自主决策 分离 热流峰值 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]