航空学报2026，Vol.47Issue(17)：66-72,7.DOI:10.7527/S1000-6893.2025.32966
固体火箭超燃冲压发动机模态转换迟滞现象
Hysteresis of combustion mode transition in solid rocket scramjet engine
摘要
Abstract
To raise the level of understanding of combustion mode transition characteristics in solid rocket scramjet en-gine,direct connect test of mode transition in solid rocket scramjet engine is investigated.The flight condition of Mach number 6.0 and height of 26.0 km is simulated in direct connect test,and mass flow rate of inflow air is 4.0 kg/s.With adjusting the mass rate of fuel gas,subsonic combustion mode and supersonic combustion mode are observed in the same configuration of combustor.The max pressure of fuel gas generator in subsonic combustion mode is 3.152 MPa,the max mass flow rate of fuel gas is 0.533 kg/s,and working hours is about 7 s;the max pressure of fuel gas generator in supersonic combustion mode is 1.404 MPa,the max mass flow rate of fuel gas is 0.312 kg/s,and work-ing hours is about 11 s.The result shows that at the same air-fuel ratio(14.0,13.5,13.0),the distribution of pres-sure along the engine in subsonic combustion mode is apparently higher than that in supersonic combustion mode.This phenomenon shows that under the same inlet flow condition and engine configuration,there may be subsonic combustion mode or supersonic combustion mode,and in other words,hysteresis of combustion mode transition ap-pears.Analyzing the distribution of pressure along the engine during initial ignition stage of tests,it is found that hyster-esis of combustion mode transition is caused by difference in ignition region of fuel gas.关键词
固体火箭/超燃冲压/模态转换/迟滞现象/直连试验Key words
solid rocket/scramjet/mode transition/hysteresis/direct connect test分类
航空航天引用本文复制引用
董新刚,蔡瑞鹏,杨玉新,黄礼铿,何国强..固体火箭超燃冲压发动机模态转换迟滞现象[J].航空学报,2026,47(17):66-72,7.基金项目
国家级项目 National Level Project （）
