可重复使用液体火箭是未来航天运输系统的重要发展方向，火箭垂直再入过程中底部发动机以非规则构型迎风下降，局部热环境和流动特性十分复杂。针对猎鹰9号v1.2的构型设计箭体，根据再入过程的特点选取了高空动力减速、高空气动减速、低空气动减速、低空动力减速等四个典型阶段，开展了发动机迎风再入绕流气动特性仿真研究。结果表明，再入过程箭体热环境呈高度瞬态、非均匀特征，羽流结构随高度和发动机工况发生显著变化；动力减速阶段因燃气-来流强耦合，其流动紊乱程度与热流峰值均显著高于气动减速阶段；二次燃烧对低空远场羽流的热影响具有全域性；四个典型阶段中，最大热流始终集中于喷管出口外沿及箭体底部边缘区域，峰值可达380kW/m2，为发动机热防护设计提供支撑。
Reusable liquid-propellant launch vehicles constitute a pivotal direction for future space transportation systems. During vertical reentry, the aft-mounted engines descend in an irregular configuration facing the freestream, engendering highly localized and complex thermal environments. A simulation study of the flow over a Falcon 9 v1.2 derived geometry was conducted for four representative reentry phases: high-altitude powered deceleration, high-altitude aerodynamic deceleration, low-altitude aerodynamic deceleration, and low-altitude powered deceleration. Results demonstrate that the vehicle thermal environment is markedly transient and non-uniform: plume morphology evolves continuously with altitude and engine operating condition; powered phases exhibit substantially stronger flow disturbances and heat-flux maxima than aerodynamic phases owing to intense plume–freestream coupling; secondary combustion exerts a global thermal influence on the far-field plume at low altitude. Across all phases, peak heat flux consistently localizes at the nozzle-exit lip and the outer rim of the aft heat shield, reaching 380 kW/m2, thereby identifying these regions as critical for thermal protection.
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