Criteria for hypersonic airbreathing propulsion and its experimental verification

doi:10.1016/j.cja.2020.11.0011000-9361

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Criteria for hypersonic airbreathing propulsion and its experimental verification
	Jiang ZL(姜宗林)1,2; Zhang ZJ(张子健)1,2; Liu YF(刘云峰)1,2; Wang C(王春)1,2; Luo ZT(罗长童)1,2
刊名	CHINESE JOURNAL OF AERONAUTICS
	2021-03-01
卷号	34 期号:3 页码:94-104
关键词	Concept demonstration Hypersonic propulsion Oblique detonation engine Scramjet Shock wave Supersonic combustion Wind tunnel test
ISSN号	1000-9361
DOI	10.1016/j.cja.2020.11.0011000-9361
通讯作者	Jiang, Zonglin(zljiang@imech.ac.cn)
英文摘要	Hypersonic airbreathing propulsion is one of the top techniques for future aerospace flight, but there are still no practical engines after seventy years? development. Two critical issues are identified to be the barriers for the ramjet-based engine that has been taken as the most potential concept of the hypersonic propulsion for decades. One issue is the upstream-traveling shock wave that develops from spontaneous waves resulting from continuous heat releases in combustors and can induce unsteady combustion that may lead to engine surging during scramjet engine operation. The other is the scramjet combustion mode that cannot satisfy thrust needs of hypersonic vehicles since its thermos-efficiency decreases as the flight Mach number increases. The two criteria are proposed for the ramjet-based hypersonic propulsion to identify combustion modes and avoid thermal choking. A standing oblique detonation ramjet (Sodramjet) engine concept is proposed based on the criteria by replacing diffusive combustion with an oblique detonation that is a unique pressure-gain phenomenon in nature. The Sodramjet engine model is developed with several flow control techniques, and tested successfully with the hypersonic flight-duplicated shock tunnel. The experimental data show that the Sodramjet engine model works steadily, and an oblique detonation can be made stationary in the engine combustor and is controllable. This research demonstrates the Sodramjet engine is a promising concept and can be operated stably with high thermal efficiency at hypersonic flow conditions. ? 2020 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
分类号	二类/Q1
资助项目	National Natural Science Foundation of China[11532014]
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:000634376600004
资助机构	National Natural Science Foundation of China
其他责任者	Jiang, Zonglin
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/86440]
专题	力学研究所_高温气体动力学国家重点实验室
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China;
推荐引用方式 GB/T 7714	Jiang ZL,Zhang ZJ,Liu YF,et al. Criteria for hypersonic airbreathing propulsion and its experimental verification[J]. CHINESE JOURNAL OF AERONAUTICS,2021,34(3):94-104.
APA	姜宗林,张子健,刘云峰,王春,&罗长童.(2021).Criteria for hypersonic airbreathing propulsion and its experimental verification.CHINESE JOURNAL OF AERONAUTICS,34(3),94-104.
MLA	姜宗林,et al."Criteria for hypersonic airbreathing propulsion and its experimental verification".CHINESE JOURNAL OF AERONAUTICS 34.3(2021):94-104.