DSMC法模拟双组元姿控发动机喷管流动  

DSMC simulation of nozzle flow of bipropellant attitude control engine

作　　者：王平阳[1] 程惠尔[1] 杨卫华[1] 

机构地区：[1]上海交通大学工程热物理研究所,上海200030

出　　处：《推进技术》2003年第2期112-114,165,共4页Journal of Propulsion Technology

基　　金：高等学校博士学科点专项科研基金(No.20010248024);博士后基金资助课题

摘　　要：为了准确获得喷管内不同燃气成分的参数,采用直接模拟蒙特卡罗(DSMC)方法结合可变软球(VSS)模型模拟喷管流动。单组分的计算结果与文献比较表明,所采用的程序和计算结果可信。对真空双组元钟形喷管内流动的模拟结果表明,压强扩散和热扩散的综合效应导致质量越大的分子越趋向于向边界层内扩散。To accurately obtain the parameters of different species in a nozzle, the direct simulation Monte Carlo (DSMC) method in combination with the variable soft sphere (VSS) model was employed in the analysis of a low-density gas flow in a small nozzle. Comparison of the present results for simple gas with those of previous work in reference shows that the results are believable. Based on this, the mixed gas flow in the bell-shaped nozzle of a bipropellant engine was simulated. The results show the integrated effect of the pressure and thermal diffusion caused the heavy gases to move towards boundary layer.

关 键 词：双元推进剂火箭发动机 姿控火箭发动机 蒙特卡罗法 喷管气流 数值仿真 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程] TK121[动力工程及工程热物理—工程热物理]