Conceptual Study on Non-ablative TPS for Hypersonic Vehicles

	Conceptual Study on Non-ablative TPS for Hypersonic Vehicles
	Jiang ZL(姜宗林); Liu YF(刘云峰); Han GL(韩桂来); Jiang ZL(姜宗林)
会议录名称	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
	2011
页码	AIAA 2011-2372
会议名称	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
会议日期	APR 11-14, 2011
会议地点	San Francisco, CA, United states
摘要	In order to achieve efficient wave drag reduction under non-zero attack angles and avoid the severe aerodynamic heating, a new concept of the Non-ablative Thermal Protection System (NaTPS) for hypersonic vehicles was proposed based on the idea that the conical shock wave angle can be enlarged by lateral jets to push the conical shock away from the blunt body surface. In the NaTPS, a spike-blunt body structure and lateral jets are combined together to develop a new shock-reconstructing system in front of hypersonic vehicles. When the spike acts to recast the bow shock in front of a blunt body into a conical shock, the lateral jet works to protect the spike tip from overheating and push the conical shock away from the blunt body when a pitching angle exists during flight. The experimental flow visualization and the pressure measurements were conducted in a hypersonic wind tunnel for both the conceptual demonstration and CFD validation. Numerical simulations were also carried out to examine the complex flow around the NaTPS. Both experimental and numerical results show that the NaTPS works well for shock drag reduction and thermal protection. The shock/shock interaction on shoulders of the blunt body is avoided due to lateral jet injection and the peak pressure at the reattachment region is reduced by 65% under a 4° attack angle. The lateral jet could be powered either by high pressure gas stored in the tank or by the water evaporation process in which water absorbs the heat from the hot walls of the blunt noses. The jet pressure needed for producing lateral jet is much smaller than for the forward-facing jet from the stagnation point. The advantages of this concept are well demonstrated and its practical application appears promising.
课题组名称	LHD激波与爆轰物理
资助信息	American Institute of Aeronautics and Astronautics (AIAA)
ISBN号	978-1-60086-942-6
URL	查看原文
收录类别	EI
语种	英语
文献类型	会议论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/48287
专题	高温气体动力学国家重点实验室
通讯作者	Jiang ZL(姜宗林)
推荐引用方式 GB/T 7714	Jiang ZL,Liu YF,Han GL,et al. Conceptual Study on Non-ablative TPS for Hypersonic Vehicles[C]17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011,2011:AIAA 2011-2372.

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