Criteria for hypersonic airbreathing propulsion and its experimental verification  

作　　者：Zonglin JIANG Zijian ZHANG Yunfeng LIU Chun WANG Changtong LUO 

机构地区：[1]State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China [2]School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China

出　　处：《Chinese Journal of Aeronautics》2021年第3期94-104,共11页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (No. 11532014)。

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.

关 键 词：Concept demonstration Hypersonic propulsion Oblique detonation engine SCRAMJET Shock wave Supersonic combustion Wind tunnel test 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] V43