高超声速单/多喷管逆向喷流降热特性研究  

Counter Flowing Jet/Jets on Heat Flux Reduction for Hypersonic Vehicles

作　　者：黄喜元[1] 李小艳[1] 杨勇[1] 陈智[2] 苗文博[2] Huang Xi-yuan;Li Xiao-yan;Yang Yong;Chen Zhi;Miao Wen-bo(China Academy of Launch Vehicle Technology,Beijing,100076;China Academy of Aerospace Aerodynamics,Beijing,100074)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]中国航天空气动力技术研究院,北京100074

出　　处：《导弹与航天运载技术》2021年第4期45-49,共5页Missiles and Space Vehicles

摘　　要：作为一种主动热防护技术,逆向喷流因其可以显著地降低飞行器的气动加热环境,是未来主动热防护系统的一种有效的选择。本文重点开展逆向喷流降热技术的研究,围绕单喷管和多喷管逆向喷流降热技术,针对高超声速飞行器头部研究了两种逆向喷流降热方案的降热特性,研究表明单喷管逆向喷流降热具有局限性,多喷管逆向喷流降热更具鲁棒性和工程适应性,具有更广阔的应用前景。As one kind of active thermal protection technologies,counterflowing jet is a good choice for future thermal protection system because of its capability on heat flux reduction.The heat flux reduction of counter flowing jet is focused on.Some characteristics of heat flux reduction of two counterflowing jet schemes for the nose cap of a hypersonic vehicle are presented in detail.The results show that the feasibility of counterflowing jet on heat flux reduction for application in the nose cap of hypersonic vehicles,and that the limitation of single counter flowing jet scheme and the robustness and adaptation of double counter flowing jets in engineering.The research is important for the engineering application of counterflowing jet on heat flux reduction.

关 键 词：逆向喷流 气动加热 降热 高超声速飞行器 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]