超声速气流中的爆震推进理论与研究进展

爆震燃烧近似为等容燃烧，理论上其热循环效率高于基于等压燃烧的爆燃燃烧，在超声速推进系统中具有潜在的应用价值.通过总结超声速气流中的爆震推进理论与研究进展，分析其需要解决的关键科学与技术问题，指导未来高超声速发动机的基础研究.文章重点总结了适用于高超声速飞行的斜爆震发动机、超声速脉冲爆震冲压发动机的基础研究进展.其中对斜爆震发动机的应用模式、相关实验研究思路及方法、数值仿真现状进行了总结分析.对超声速脉冲爆震冲压发动机的基础理论研究现状和目前研究的难点进行了梳理.基于爆震燃烧的超燃冲压发动机具有推进系统自增压、燃烧效率高、推力性能好、推进效率高、燃烧室长度短、结构重量轻等优势，文章总结了该发动机当前的发展进程和最新的研究进展，并对其未来的发展方向以及存在的技术问题进行了分析. 

Theory and Research Progress of Detonation Propulsion in Supersonic Flow

Detonation cycle is an isochoric Fickett-Jacobs thermodynamic cycle, while the deflagration cycle is an isobaric Brayton-Joule one. The thermodynamic efficiency of Fickett-Jacobs cycle is higher than that of the Brayton-Joule, which is a main motivator for the applications of detonative combustion to the supersonic propulsion system. This paper summarized the results of theory and progress for detonation propulsion in supersonic flow, and analyzed the remaining scientific and technological problems, providing a guidance for the future investigations on hypersonic engines. The development of oblique detonation engine (ODE) and supersonic pulsed detonation ramjet engine (SPDRE) was reviewed. For the ODE, the application modes of ODE, the methods of experimental investigation, and the development of numerical studies were summarized. For the SPDRE, the current status and difficulties were reviewed. The detonation driven scramjet engines are advantageous for the self-pressurization, high combustion efficiency, high thrust performance, high propulsive efficiency, short chamber length, and light weight. The development and current progress were summarized, and the future development direction and technical problems were analyzed.