火箭推进2026，Vol.52Issue(4)：20-32,13.DOI:10.3969/j.issn.1672-9374.2026.04.003
垂直再入火箭底部发动机流动和热环境特性研究
Simulation study on flow and thermal environment characteristics of reuseable rocket's engine during vertical reentry process
摘要
Abstract
The force and thermal environment characteristics of a reusable rocket's engine are extremely complex during reentry.Based on the characteristics of the reentry process,four typical operating conditions,namely a typical high-altitude propulsive deceleration condition,the highest speed point and the maximum dynamic pressure point during aerodynamic deceleration,and a typical condition of low-altitude propulsive deceleration,were selected for simulation research.The results reveal significant differences in the flow and thermal environment across different stages of the engine reentry process.During the propulsive deceleration phase,the interaction between the gas jet and the oncoming reverse flow is more complex than the flow field of aerodynamic deceleration phase.During the propulsive deceleration phase,the local heat flux on the external wall of the engine exceeds 200 kW/m2,while the peak local heat flux during the aerodynamic deceleration phase is approximately 30 kW/m2.Furthermore,significant differences exist in the external wall heat flux distribution of the engine between propulsive deceleration phase and aerodynamic deceleration phase.And there are also notable differences in the external wall heat flux distribution between high-altitude propulsive deceleration phase and low-altitude propulsive deceleration phase.At the maximum dynamic pressure point of the aerodynamic deceleration phase,the pressure load on the external wall of the engine is the most severe.关键词
液体火箭发动机/多机并联/垂直再入/流动特性/热环境Key words
liquid rocket engine/multi-engine/vertical reentry/flow characteristics/thermal environ-ment分类
航空航天引用本文复制引用
胡亚豪,刘阳旻,李晶茹,李子亮,许晓勇,刘曌俞..垂直再入火箭底部发动机流动和热环境特性研究[J].火箭推进,2026,52(4):20-32,13.基金项目
民用航天预先研究项目(DXXXX01) （DXXXX01）
