大空域、宽速域条件下高超声速飞行器喷流反作用控制系统（RCS）的喷流二次燃烧效应难以快速准确预测。本项目以典型锥-柱-裙构型高超声速飞行器为研究对象，开展多物理场高保真数值仿真研究，系统分析不同马赫数和飞行高度下喷流二次燃烧对飞行器气动力特性的影响规律，提出适用于喷流二次燃烧快速模拟的简化化学反应模型。研究表明：喷流二次燃烧效应显著影响压力系数分布，仿真结果与文献结果最大误差不超过15%，简化化学反应模型可以使得化学反应源项计算时间缩短50%，在4-15 Ma速度条件和15-40 km高度条件下，推力放大因子随着马赫数增加而增加，随着高度增加而下降。本项目的研究结果可为喷流反作用控制系统性能预测提供重要参考。

Under conditions of wide operational envelopes, the secondary combustion effects of the jet in the reaction control system (RCS) of hypersonic vehicles are difficult to predict quickly and accurately. Focusing on a generic cone-cylinder-flare hypersonic configuration, this study conducts high-fidelity multiphysics numerical simulations to systematically investigate the impact of jet secondary combustion on the aerodynamic characteristics under varying Mach numbers and flight altitudes. To accelerate the simulation process, a simplified chemical reaction model tailored for RCS jet secondary combustion is proposed. Research shows that the secondary combustion effect of the jet significantly affects the distribution of pressure coefficients. The simulation results have a maximum error of no more than 15% compared with literature results. The simplified chemical reaction model can reduce the computation time of the chemical reaction source term by 50%. Under speed conditions of 4-15 Ma and altitude conditions of 15-40 km, the thrust amplification factor increases with Mach number and decreases with altitude. These findings provide a crucial theoretical reference for the performance prediction and design optimization of jet-based reaction control systems.