Standing oblique detonation is a unique pressure-gain combustion phenomenon for hypersonic ramjet propulsion, and its research has been related with supersonic combustion in scramjet engines since its births, for example, absent treatment in its early stage and re-consideration in recent decades. Standing oblique detonations and supersonic combustion share the same features of supersonic chemically-reacting flows, and can be considered as different flow development stages. Combustion instability in a chemically-reacting flow is reviewed first to identify its fundamental mechanisms, and the upstream-propagating shock wave is identified as one of intrinsic characteristics and taken as the key problem for developing hypersonic ramjet propulsion. Critical conditions for the standing oblique detonation are summarized as a theoretical base for standing oblique detonation ramjet engines. Three key parameters are included, that is, the maximum heat that can drive local flow states from supersonic to sonic after combustion, the critical inflow Mach number of combustors, at which supersonic combustion becomes stable, and the critical wedge angle at which a standing oblique detonation can be initiated. The evolution of the standing oblique detonation is reviewed by placing emphasis on its complex wave structure that was found to develop via three stages, that is, shock-induced initiation, the decaying stage and the fully-developed stage. Finally, progress in experimental research is reviewed with detailed discussions on stabilization of the standing oblique detonation, experimental methods and development of adequate test facilities. In conclusion, the stable operation of hypersonic ramjet propulsion is a critical issue to approach its engineering application, and the standing oblique detonation ramjet engine is recommended as a promising candidate, deserving more attention in the future.

直立斜爆是高超声速冲压发动机推进中一种独特的增压燃烧现象，其研究从诞生之日起就与超燃冲压发动机中的超声速燃烧相关，例如早期的缺失和近几十年来的重新考虑。直立斜爆和超音速燃烧具有超音速化学反应流的相同特征，可以认为是不同的流动发展阶段。首先回顾了化学反应流中的燃烧不稳定性，以确定其基本机制，并将上游传播的冲击波确定为固有特征之一，并将其​​作为发展高超声速冲压发动机推进的关键问题。总结了直立斜爆的临界条件，为直立斜爆冲压发动机提供了理论基础。包括三个关键参数，即燃烧后局部流动状态由超音速转变为音速的最大热量、超音速燃烧稳定时燃烧室的临界流入马赫数、立斜楔角。可以引发爆炸。回顾了直立斜爆的演化过程，重点关注其复杂的波结构，发现其发展经历了三个阶段，即激波引发、衰变阶段和完全发展阶段。最后，回顾了实验研究进展，详细讨论了直立斜爆的稳定性、实验方法和适当测试设施的开发。综上所述，高超声速冲压发动机推进的稳定运行是其工程应用的关键问题，立式斜爆冲压发动机是一种有前景的候选发动机，值得未来更多的关注。