Concept of non-ablative thermal protection system for hypersonic vehicles

doi:10.2514/1.J051875

	Concept of non-ablative thermal protection system for hypersonic vehicles
	Liu YF(刘云峰); Jiang ZL(姜宗林); Jiang, ZL (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China.
发表期刊	AIAA Journal
	2013-03
卷号	51 期号:3 页码:584-590
ISSN	0001-1452
摘要	In order to reduce the shock-wave drag and aerodynamic heating of hypersonic vehicles effectively a new concept of non-ablative thermal protection system was proposed based on the idea of flowfield reconstruction. In this non-ablative thermal protection system a spike-blunt body structure and lateral jets are combined together to realize the flowfield modification. The spike transforms the bow shock into a conical shock, and the lateral jets increase the angle of conical shock wave and keep it away from the blunt body to avoid severe shock/shock interactions. Flow visualizations and pressure measurements were conducted in a hypersonic wind tunnel at Mach number 6 to demonstrate this concept. Numerical simulations were also carried out. Both experimental and numerical results demonstrate that the non-ablative thermal protection system works well for shock-wave drag reduction and thermal protection. The peak pressure at the reattachment region is reduced by 65% even under 4 deg attack angle by the lateral jet. Experimental data also show that the working pressure of lateral jets is much lower than that of forward-facing jets at the stagnation point. All the results show that the engineering application of non-ablative thermal protection system appears to be quite promising.
关键词	Flow Fields Flow Visualization Hypersonic Aerodynamics Hypersonic Vehicles Mach Number Shock Waves Thermal Insulating Materials Engineering Applications Experimental Datum Hypersonic Wind Tunnels Numerical Results Stagnation Points Thermal Protection Thermal Protection System Working Pressures
学科领域	空气动力学
DOI	10.2514/1.J051875
URL	查看原文
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:000315551200004
关键词[WOS]	WAVE DRAG REDUCTION ; HEAT-TRANSFER ; ENERGY DEPOSITION ; SUPERSONIC-FLOW ; SHOCK-WAVE ; MITIGATION ; BODIES ; SPIKE ; JET
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
项目资助者	Y210061021
课题组名称	LHD激波与爆轰物理
论文分区	一类
引用统计	被引频次：42[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/47144
专题	高温气体动力学国家重点实验室
通讯作者	Jiang, ZL (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temperature Gas Dynam, Beijing 100190, Peoples R China.
推荐引用方式 GB/T 7714	Liu YF,Jiang ZL,Jiang, ZL . Concept of non-ablative thermal protection system for hypersonic vehicles[J]. AIAA Journal,2013,51,3,:584-590.
APA	Liu YF,Jiang ZL,&Jiang, ZL .(2013).Concept of non-ablative thermal protection system for hypersonic vehicles.AIAA Journal,51(3),584-590.
MLA	Liu YF,et al."Concept of non-ablative thermal protection system for hypersonic vehicles".AIAA Journal 51.3(2013):584-590.

条目包含的文件		下载所有文件
文件名称/大小	文献类型	版本类型	开放类型	使用许可
IMCAS-J2013-012.pdf（5046KB）			开放获取	--	浏览下载