摘要
应用脉冲枪不稳定燃烧模型对有 /无声腔的MMH/NTO火箭发动机的燃烧稳定性进行了数值模拟 ,比较了 3台MMH/NTO发动机的燃烧动态稳定性 ,计算与发动机的试车结果一致。
A given MMH/NTO rocket engine combustion stability with/without acoustic cavities was numerically simulated by pulse gun combustion instability model. Three MMH/NTO rocket engines combustion dynamic stabilities were compared and assessed. Numerical simulation and assessment results are agreeable with the engine hot test data.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2001年第2期155-156,164,共3页
Journal of Propulsion Technology
基金
国家"八六三"基金资助项目
