摘要
在考虑N2O4/一甲基肼(MMH)自燃推进剂雾化、蒸发和化学反应过程的条件下,采用贴体网格系统和耦合显式求解算法,仿真计算了小推力液体发动机不同喷嘴设计对推进剂的蒸发、混合燃烧、推力室内流场和燃烧室效率的影响。仿真结果与高空热试车数据基本一致。所用模型合理,具一定的参考价值。
Under the consideration of atomization, evaporation and chemical reaction process of N2O4/MMH propellant, the effect of nozzle design on the evaporation, mixed combustion of the propellant, inner flowfield of the thrust in chamber, and efficiency of the combustion chamber for small thrust liquid engine was calculated using the explicit coupled solver algorithm with closed grid in this paper. The numerical simulation results were generally agreed with the data of altitude hot firing. The model used was reasonable, which was valuable in the chamber modified design.
出处
《上海航天》
北大核心
2007年第6期39-43,共5页
Aerospace Shanghai
关键词
小推力液体发动机
喷嘴
燃烧室效率
数值模拟
Small thrust liquid engine
Nozzle
Combustion performance
Numerical simulation
