可回收火箭的热度在逐年上升，而其结构设计面临着严酷的热环境考核。目前，数值模拟被认为飞行器设计阶段有效手段之一，然而发射阶段火箭壁面与地面受气流热效应影响机制还尚不明确。因此针对某可回收火箭地面发射过程，采用动边界计算流体力学（computational fluid dynamics, CFD）技术及多组分模型开展尾部高温燃气发展及其对地面和箭体热环境影响的动态数值模拟研究。结果表明：在近地面位置发射初期，地面持续受到2.5×10⁷ W/m²以上的冷壁热流持续冲刷，其中对流传热占据主导；而箭体底部最大对流热流密度和辐射热流密度分别可35 000 W/m²和60 000 W/m²；火箭离地后随高度增加对流热流密度与辐射热流密度都呈减小的趋势，且辐射传热在该过程中对该部位的影响占据主导。

The temperature of reusable rockets has been steadily increased, and their structural design is subjected to stringent thermal environment assessments. Currently, numerical simulations are considered one of the effective tools during the design phase of spacecraft. However, the mechanisms of thermal effects caused by airflow on the rocket's surface and the ground during the launch phase are not yet well understood. Therefore, the ground launch process of a particular reusable rocket was investigated through the employment of dynamic boundary computational fluid dynamics (CFD) techniques and a multi-component model, through which a dynamic numerical simulation was conducted to analyze the development of high-temperature exhaust gases and their impact on the thermal environment of both the ground and the rocket body. The results demonstrate that during the early stage of launch at near-ground positions, the ground is continuously subjected to a cold-wall heat flux exceeding 2.5 × 10⁷ W/m², with convective heat transfer being identified as the dominant mode. The maximum convective heat flux density and radiative heat flux density at the bottom of the rocket body are found to reach 35 000 W/m² and 60 000 W/m², respectively. After the rocket is lifted off, both the convective heat flux density and radiative heat flux density are observed to decrease with increasing altitude, with radiative heat transfer being established as the dominant mode at this stage.