摘要
针对固体火箭发动机大膨胀比喷管出现的侧向载荷,采用三维数值仿真方法进行分析。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,结合FLUENT中UDF功能,对燃气流动与喷管结构运动变形进行了耦合计算。计算结果发现,此大膨胀比喷管在快速升压阶段先后经历了自由激波分离和受限激波分离;分析得出了较强的侧向载荷主要由不对称的燃烧波、激波转变和喷管出口部位的激波震动3种状态产生;侧向载荷的大小也与快速升压的时间快慢有较大关系。采用流固耦合计算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,为更深入研究大膨胀比喷管侧向载荷提供了支撑。
A side load in the overexpanded nozzle was studied by means of a three dimensional numerical simulation method. The MpCCI software was used to link the FLUENT CFD code whose UDF is applied with the ABAQUS FE code to analyze gas flow and nozzle deformation. Results show that three types of asymmetric shock physics incur strong side loads： the generation of com bustion wave, shock transitions, and shock pulsations across the nozzle lip. Moreover, the ramp time results show that the ramp rate has the potential effect on the nozzle side loads. The fluid structure coupled numerical simulation support the accuracy of the meth- od 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4期463-467,473,共6页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
大膨胀比喷管
快速升压
侧向载荷
流固耦合
solid rocket motor
over-expanded nozzle
rapid pressurization
side load
fluid-structure coupled analysis
