固体发动机喷管延伸锥展开前级间分离的热环境分析  

The thermal condition analysis of stage separation for a multistage solid rocket before the nozzle exit cone extend

作　　者：韩丽霞[1] 田维平[1] 乐发仁[1] 余贞勇[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2004年第1期12-15,共4页Journal of Solid Rocket Technology

摘　　要：通过FLUENT流场计算软件,采用RNGκ ε湍流模型,针对带有延伸喷管的多级固体发动机级间热分离的热环境进行了数值分析。研究表明,延伸喷管尾流受到连接筒、前封头、延伸段的阻碍后,其流动特征变化显著,尤其在一级前封头的影响下形成回流,并在喷管内形成激波。计算得到的热环境参数,对发动机的热防护设计具有一定的参考价值。The thermal condition of stage separation for a multistage solid rocket with extendible nozzle was analyzed by means of flow computation softwave FLUENT and the turbulent flow model RNG κ-ε. The results indicate that characteristics of the wake flow in the extendible nozzle change significantly when the wake flow is blocked by the adapter cylinder, the foward dome and the exit cone, especially when a backflow comes into being due to effect of the foward dome of the first stage motor and a shock wave forms in the nozzle. The thermal condition parameters calculated can provide references to the thermal-protection design of the solid motor.

关 键 词：固体发动机 喷管延伸锥 级间分离 热环境分析 边界条件 

分 类 号：V435.1[航空宇航科学与技术—航空宇航推进理论与工程]