摘要
为了研究某型运载火箭发射流场的特征,采用计算流体力学(computational fluid dynamics,CFD)技术对某型运载火箭飞行5 m工位下的流场进行数值模拟。以3维单喷管发动机为模型,选用标准k-ε湍流模型,同时考虑混合气体,获得发动机尾焰流场,分析尾焰波系结构随时间的变化。计算结果表明:单喷管轴对称模型下的流场各个参数分布、激波系结构与理论分析结果一致,可为后续相关实验测量提供参考和理论依据。
In order to study the characteristics of fluid field of certain type launch vehicle, the numerical simulation of the flow field of a launch vehicle under 5 m workstation was conducted with CFD（Computational Fluid Dynamics） technique. Based on the 3 D single nozzle engine model, with the standard k-e turbulence model, the mixed gas flow was considered, and then, the flow field of engine tail flame was obtained, the change of the plume wave structure with time was analyzed. The results showed that the parameters of the flow field and the structure of the shock wave system are consistent with the theoretical analysis results, which provide a reference and theoretical basis for the subsequent experimental measurements.
作者
李志刚
周珊
王华
Li Zhigang;Zhou Shan;Wang Hua(School of Mechanical Engineering,Nanjing University of Science ＆ Technology,Nanjing 210094,China;No.7 Design Department of No.7 Research InstitutG China Aerospace Science ＆ Technology Group Co.,Ltd.,Chengdu 610000 China)
出处
《兵工自动化》
2018年第6期93-96,共4页
Ordnance Industry Automation
关键词
运载火箭
发射流场
单喷管
混合气体
launch vehicle
launch flow field
single nozzle
mixed gas
