The shock-induced combustion ramjet engine is the most favorable air breathing propulsive system and a suitable option for high-speed flight. In this paper, theoretical analysis and numerical simulations were conducted to study the thrust performance of shock-induced combustion ramjet engines. Firstly, the propulsive performance of supersonic combustion ramjet engines was theoretically analyzed by using the Chapman-Jouguet detonation theory. Then, the aerodynamic principles of shock-induced combustion ramjet engines were put forth on the basis of the theoretical analysis results. Finally, a full-scale shock-induced combustion ramjet engine was designed according to the aerodynamic principles. Two-dimensional numerical simulations were conducted to simulate its combustion flow field and propulsive performance. The numerical results demonstrate the correctness and application of the theoretical aerodynamic principles.

激振燃烧冲压发动机是最有利的空气推进系统，是高速飞行的合适选择。本文通过理论分析和数值模拟研究了冲击诱导燃烧冲压发动机的推力性能。首先，利用Chapman-Jouguet爆轰理论对超音速冲压发动机的推进性能进行了理论分析。然后，在理论分析结果的基础上，提出了冲击诱导式冲压发动机的空气动力学原理。最后，根据空气动力学原理设计了一种全尺寸冲击诱导燃烧冲压发动机。进行了二维数值模拟，以模拟其燃烧流场和推进性能。