摘要
针对固体火箭发动机大膨胀比喷管出现的分离流动,采用数值仿真方法进行分析,并与试验进行对比。通过集成软件平台MpCCI,连接计算流体动力学软件FLUENT和有限元软件ABAQUS,对燃气流动与喷管结构运动变形进行了耦合计算。耦合计算结果发现,此大膨胀比喷管发生气流分离,且分离处斜激波后的气流温度与压力变化较大,采用流固耦合数值方法能体现喷管的结构变形,从而更准确地反映喷管与燃气流相互影响的真实环境。耦合计算结果与试验进行对比得出,耦合计算得到的分离位置能很好地拟合实验测得的气流分离位置,说明了流固耦合数值方法的有效性,为更深入研究大膨胀比喷管分离流动现象提供了支撑。
The flow separation in the overexpanded nozzle was studied by using numerical simulation method and compared with experiment result.The MpCCI software is used to link the FLUENT CFD code and the ABUQUS FE code to analyze gas flow and the nozzle deformation.The results show that the gas in the nozzle is separated and the dramatic temperature and pressure alteration occur in the separation zone.The location of the separation point of fluid-structure coupled simulation was similar to the experimental data and can display the nozzle deformation,which support the accuracy of the method of numerical simulation.The simulation provides the base for further study.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第3期344-347,381,共5页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
大膨胀比喷管
分离流动
流固耦合分析
solid rocket motor
over-expanded rocket nozzle
flow separation
fluid-structure coupled analysis
