战术火箭子母战斗部第一次抛撒分离多体干扰流场数值模拟  

Numerical Investigation of Multi-Body Flow Fields in the First Separation of Tactical Rocket's Submunitions

作　　者：雷娟棉 苗瑞生[1] 居贤铭[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《北京理工大学学报》2004年第9期766-769,785,共5页Transactions of Beijing Institute of Technology

基　　金：国家部委预研项目(413130305)

摘　　要：以三维Navier-Stokes方程为基础,用计算流体力学(CFD)数值模拟方法对俄9M55K型火箭弹子母战斗部的第一次抛撒分离过程——子弹筒从母弹侧向抛出进行了研究.数值模拟结果表明,当子弹筒离母弹很近时,子弹筒头部激波在母弹上的反射是母弹对子弹筒气动干扰的主要原因;当子弹筒穿越母弹头部激波时,母弹头部激波是引起子弹筒气动特性剧烈变化的主要原因;多个子弹筒相距较近时,子弹筒头部激波之间的彼此干扰也很重要.这些结论可为子母型武器的总体设计、分离参数选择提供气动依据.Based on the three-dimensional Navier-Stokes equations, computational fluid dynamics(CFD) numerical simulation was used to investigate the multi-body flow field in the first separation of tactical rocket 9M55K, where the submunition tube separate from the side of the main rocket. Numerical simulation results show that the main aerodynamic interference was caused by the head shock wave reflections of the submunition tube from the main rocket, while the submunition tube was close to the main rocket, but the action of the main rocket head shock wave on the body of the submunition tube is the main reason that makes the aerodynamic characteristics of the submunition tube varied acutely while the submunition tube apart from the main rocket. Simulation results also show that there are fairly strong aerodynamic interferences between the submunition tubes while they are closed to each other. These conclusions can be taken as basis in the overall design and the selection of separate parameters for munitions with multiple submunitions.

关 键 词：子母弹 多体分离干扰 数值模拟 气动特性 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]