微型脉冲固体火箭发动机侧喷流数值仿真  

Numerical Simulation of Lateral Jet of Micro Pulse Solid Rocket Motor

作　　者：张涵[1] 吴达[1] 王旭东[1] 汪汝根 

机构地区：[1]空军工程大学防空反导学院,西安710051

出　　处：《弹箭与制导学报》2016年第6期92-96,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航空科学基金(20130196004)资助

摘　　要：针对不同工况条件下的微型脉冲固体火箭发动机侧喷流外流场进行两相流条件仿真研究,除了对不同导弹攻角条件下的两相流进行分析,还探究了弹体表面参数受颗粒的影响情况。研究结果表明:在同一颗粒质量分数条件下,颗粒直径越小,对喷流的控制效果产生消极影响越大;在两相流情况下,颗粒相对干扰流场的结构产生了较大影响,颗粒相对喷流的控制效果起消极作用;导弹处于正攻角时,有利于喷流控制作用,攻角越大,控制效果越好。The simulation of two-phase flow conditions in the lateral jet flow field of micro pulse solid rocket engine under different operating conditions was carried out,in addition to analyze two-phase flow at different missile attack angle conditions,and the condition of the surface parameters of missile body influenced by particles was also analyzed.The result of research showed that,under the same particle mass fraction conditions,the smaller the particle diameter,the greater negative influence on the control effect of the jet flow.In the case of two-phase flow,the partile phase had a great influence on the structure of the flow field,and the particle played a negative role in the control of jet flow.When the missile is at the positive angle of attack,it is good for the jet control function,the greater the angle of attack,the better control effect.

关 键 词：两相流 数值模拟 侧喷流 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]