航空学报2026，Vol.47Issue(8)：106-119,14.DOI:10.7527/S1000-6893.2025.32772
液体火箭反推进再入过程底部热环境与流动特性
Base-region thermal environment and flow characteristics of liquid rocket in retro-propulsion re-entry process
摘要
Abstract
Reusable liquid-propellant launch vehicles constitute a pivotal direction for future space transportation sys-tems.During vertical re-entry of a rocket,the aft-mounted engines descend in an irregular configuration facing the freestream.The local thermal environment and flow characteristics are highly complex.A simulation study of the flow over a Falcon 9 v1.2 derived geometry was conducted for four representative re-entry phases:high-altitude powered deceleration,high-altitude aerodynamic deceleration,low-altitude aerodynamic deceleration,and low-altitude powered deceleration.The vehicle thermal environment is markedly transient and non-uniform:plume morphology evolves con-tinuously with altitude and engine operating condition.Powered deceleration phases exhibit substantially stronger flow disturbances and heat-flux maxima than aerodynamic deceleration phases owing to intense plume-freestream cou-pling.Secondary combustion exerts a global thermal influence on the far-field plume at low altitude.Across the four characteristic stages,the peak heat flux persistently localizes at the nozzle lip and the aft-edge of the rocket base,reaching 380 kW/m2,these data constitute a quantitative basis for engine thermal-protection design.关键词
可重复使用/火箭回收/垂直再入/热环境/流动特性Key words
reusable/rocket recovery/vertical re-entry/thermal environment/flow characteristics分类
航空航天引用本文复制引用
郑昊,唐勇,陈湘男,李霁,林志强,石保禄..液体火箭反推进再入过程底部热环境与流动特性[J].航空学报,2026,47(8):106-119,14.基金项目
民用航天技术预先研究项目(D020201) Civil Aerospace Technology Pre-Research Project(D020201) （D020201）
