多喷管斜切式火箭发动机流场与轴向推力研究  

Numerical Simulation of Flow Field and Study of Axial Thrust in Scarfed Nozzles of Multi-nozzle SRM

作　　者：邢鹏涛[1] 王中[1] 舒慧明[1] 古呈辉[1] 朱佳佳[1] 许云志[1] 

机构地区：[1]西安近代化学研究所,西安710065

出　　处：《弹箭与制导学报》2016年第1期116-120,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为研究多喷管斜切式火箭发动机喷管工作特点,采用有限体积法雷诺平均N-S方程,对其流场进行了三维数值模拟;并对发动机轴向推力进行了计算,将理论计算曲线与试验曲线进行了分析对比。结果表明:斜切式多喷管基本喷管段流场参数变化趋势与普通喷管基本一致,斜切喷管出口处的参数分布呈现三维偏心现象;轴向推力理论计算结果略偏大,计算曲线与试验曲线吻合较好。数值模拟结果能正确反应喷管内流动特点。In order to investigate work characteristics of scarfed nozzle of multi-nozzle SRM,the fluid field of nozzles was numerically simulated by solving a three-dimensional Reynolds-averaged Navier-Stokes equations based on the vinite volume method,and the axial thrust curve of the SRM which was calculated by using results of the numerical simulation was compared with the experimental curve. The results show that the parameters of the flow field of the main parts of the scarfed nozzles are similar to that of common nozzles,however,the parameters of the fluid field of the existing sections of the scarfed nozzles show off-centre appearance. Theoretical data of the axial thrust of the SRM are more bigger than the experimental ones,and the curve of theoretical axial thrust is well consistent with the experimental one.The simulation results can accurately reflect the flow characteristics within the nozzles.

关 键 词：斜切喷管 火箭发动机 数值模拟 轴向推力 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]