随着连续旋转爆震技术相关研究的深入开展，其性能优势逐步得到认可，同时，其应用成熟度也不断提升。近年来，有关连续旋转爆震技术在吸气式动力系统中的应用研究吸引了学术界和工业界越来越多的关注。本文以吸气式旋转爆震发动机为研究对象，构建考虑部件相容性的发动机系统方案，探索旋转爆震燃烧室反压回传及抑制方法，发展旋转爆震燃烧室低阶计算模型，在此基础上建立吸气式旋转爆震发动机参数化性能分析模型，通过发动机总体性能的理论分析，揭示基于连续旋转爆震的吸气式动力系统的性能优势及其内在机制。以期为推进连续旋转爆震技术在空天动力中的应用提供理论支撑。基于旋转爆震燃烧室喷注过程与爆震波后压力衰减过程的匹配关系，建立一种自洽的旋转爆震燃烧室低阶模型IPDM，并验证了多环腔布局在拓展燃烧室稳定工作范围和改善出口参数均匀度方面的优势。通过分析来流参数、喷注参数、燃料/氧化剂类型对旋转爆震燃烧室增压特性的影响，揭示了旋转爆震燃烧室具有增压特性的前提是旋转爆震过程的总压增益足以克服喷注过程的总压损失。基于数值模拟，获得了旋转爆震燃烧室的反压回传特征，并提出一种在内流道外壁设置障碍物的隔离段方案。通过分析隔离段几何参数对回传反压抑制效果和总压损失的影响规律，进一步确定了该隔离段的几何参数选取准则。基于旋转爆震燃烧室IPDM模型，发展双流道多环腔旋转爆震涡轮发动机参数化性能分析模型。旋转爆震涡轮发动机与常规燃气涡轮发动机的性能比较表明，在宽广的增压比范围内，前者的比推力均有显著优势，仅在增压比较低时，前者的热效率和耗油率才具有优势。带旋转爆震涵道燃烧室的涡扇发动机性能分析表明，开启旋转爆震涵道燃烧室后，发动机的推力和耗油率均显著提升，且推力比和耗油率比与风扇压比负相关，与涡轮前温度正相关。发展了旋转爆震冲压发动机和吸气式旋转爆震组合循环发动机参数化性能分析模型。与常规冲压发动机相比，旋转爆震冲压发动机具有更优的低速性能。对于吸气式旋转爆震组合循环发动机，提出一种“等推力等流量”模式转换策略，其模式转换起始马赫数越高，过渡态比推力越小、比冲越高，在满足推力需求的情况下应尽可能选择大的模式转换起始马赫数。

With the accumulation of the achievements on rotating detonation technology, the potential advantages of the rotating detonation combustor (RDC) are gradually approved, and the technical maturity of the rotating detonation technology is improved constantly. In recent decades, the application of rotating detonation technology in airbreathing propulsion systems has attracted significant interest in both academia and industry. This study focuses on the continuous rotating detonation based airbreathing propulsion systems, and the architectures for the propulsion systems with compatibility between the turbomachinery and RDC being realized are presented. The propagation of feedback pressure perturbation from the RDC is investigated and a preliminary configuration for the isolator is designed to weaken such feedback pressure perturbation. A reduced order model of the RDC, which avoids spatial discretization and solving differential equations, is developed, and the parametric analysis model for the propulsion systems based on continuous rotating detonation are established. Based on the comprehensive performance analysis of the airbreathing rotating detonation propulsion systems, the potential performance benefits as well as their generation mechanism are revealed. It is expected that the conclusions of this study can be used as theoretical foundations for promoting further development and application of the rotating detonation technology in airbreathing propulsion systems.A self-consistent reduced order model of the RDC is developed according to the matching relationship between the injection process and pressure decay (IPDM) after the detonation front. Based on this model, the potential advantages of the multi-annular rotating detonation combustor to widen the stable operation range and improve the parameter distribution at the outlet section are presented. The promise of total pressure gain being generated in the rotating detonation combustor, which can be expressed as the pressure gain of the rotating detonation process being sufficient to overcome the pressure loss generated by the injection process, is revealed by summarizing the effects of inlet parameters, injection parameters and reactant compositions on the pressure gain characteristic of the RDC.The propagation of feedback pressure perturbation generated by the RDC is revealed based on computational fluid dynamics method, and a form of isolator configuration, which is a cylinder with several rows of wedge obstacles in the inner wall, is constructed aiming at weakening the pressure perturbation. Furthermore, a preliminary optimization design criterion of the isolator is proposed based on balance between the feedback pressure reduction and total pressure recovery.A performance simulation model of the dual-duct rotating detonation aero-turbine engine is established on the basis of the reduced order model of the rotating detonation combustor. Comparisons between the rotating detonation turbine engine and the conventional turbojet engine reveal that, the former holds significant improvement in specific thrust over a wide range of pressure ratios, while exhibits improvement in efficiency and fuel consumption only at low pressure ratios. Furthermore, the study regarding the application of rotating detonation duct burner in turbofan is performed. The results show that, the thrust and specific fuel consumption increase significantly, and the thrust ratio and fuel consumption ratio are positively correlated with the turbine inlet temperature, and are negatively correlated with the fan pressure ratio.The parametric performance analysis models of the rotating detonation ramjet engine and the airbreathing combined cycle engine based on rotating detonation are developed. Compared to the conventional ramjet engine, the rotating detonation ramjet engine exhibits obvious improvement in overall performance in low flight Mach number regime. A mode transformation strategy with the thrust and freestream mass flow rate remaining constant is proposed for the airbreathing combined cycle engine based on rotating detonation. The performance characteristic during the transition mode is investigated. The results show that, the higher the initial Mach number of mode transformation, the lower the specific thrust and the higher the specific impulse of the transition mode. Therefore, a higher initial Mach number of mode transformation is the preferred choice under the premise that the thrust requirement is satisfied.