二级火箭喷流对底部热环境影响的数值模拟  

Numerical Simulation on Secondary Launcher Exhaust Plume Base Heating

作　　者：杨帆[1] 王平阳[1] 包轶颖 李鹏 

机构地区：[1]上海交通大学机械与动力工程学院,上海200240 [2]上海宇航系统工程研究所,上海201108

出　　处：《上海航天》2009年第5期46-51,共6页Aerospace Shanghai

摘　　要：为研究二级火箭工作时对底部热环境的影响,在不同喷管固壁热辐射和飞行高度条件下,用Fluent软件自发动机喷管喉部处计算喷流流场和底部区域内给定平面的对流热流密度,并建立了三维反向蒙特卡罗(RMC)法模型,同时根据HITRAN数据库计算气体红外辐射特性,获得喷流对给定平面的辐射热流密度,两者相加即为喷流到达研究平面的总热流密度。结果表明:热辐射和热对流在底部产生的热效应趋势不同。In order to evaluate the base heating environments of the secondary launcher, the exhaust plume flow field and the convective heat flux in the base region of the rocket engine were computed from the nozzle throat using Fluent software with various the effect of the nozzle wall and altitude of the rocket in this paper. The 3-D model using reverse Monte Carlo method was developed, and the infrared radiation charaeteristic of the plume gas was computed using HITRAN database to obtain the radiation heat flux in the same region. The total heat flux that could reach the base region was obtained by adding the two fluxes. The results showed that the trends of the infrared radiation and radiation heat flux were different.

关 键 词：二级火箭 喷流流场 反向蒙特卡罗法 底部热环境 对流热流密度 辐射热流密度 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]