摘要
以一维管道瞬变流理论和特征线方法为基础,建立了仿真系统部件流体动力学模型。计算方法采用带内插的特征线方法和四阶龙格库塔法。对燃烧室模型,考虑燃烧时滞的影响,计算了卫星推进系统发动机在启动过程中各参数的变化。仿真结果与卫星推进系统热试车试验结果基本吻合。结果表明计算模型较好地描述了发动机启动过程中的水击和管流振荡现象,采用的仿真方法符合精度要求,在工程上可为卫星推进系统的设计与试验提供指导。
The analytical model was developed using the water hammer and one-dimensional fluid transient theory. The combustion time delay was considered. All system parameter changes during the propulsion system engine starting process were considered. The characteristic method and the classical Runge-Kutta method were adopted for simulation. The simulation results are consistent with experiments. The results show that these models give reasonable descriptions for water hammer and flow oscillation during engine starting process. The simulation methods meet the accuracy requirements and could provide guidance for designs and experiments of propulsion system.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第4期698-701,共4页
Journal of Aerospace Power
关键词
航空
航天推进系统
数值仿真
燃烧时滞
水击
管道
特征线方法
龙格库塔法
aerospace propulsion system
numerical simulation
combustion time delay
water hammer
channel
characteristics method
Runge-Kutta
