飞行参数对射流矢量喷管内流场影响的数值模拟  

Numerical simulation on effects of flight parameters on internal flow of jet vector nozzle

作　　者：吴雄[1] 吴敏 张健 张为华 

机构地区：[1]海军装备研究院航空装备论证研究所,上海200436 [2]总装驻娄底地区军代室,湖南娄底417000 [3]总装驻孝感地区军代室,湖北孝感432100 [4]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2009年第2期234-239,共6页Journal of Propulsion Technology

基　　金：武器装备预研基金(9140A28010806KG0189);国家"八六三"高新技术项目资助(2005AA765030)

摘　　要：采用三维雷诺平均N-S方程和k-ε湍流模型对固体火箭发动机燃气二次喷射矢量喷管内外流场进行数值模拟,研究飞行参数对矢量喷管内主/次流耦合流场的影响。结果表明,自由来流造成喷管出口附近压力变化,通过喷管内壁面附面层作用影响喷管内部流动特性。飞行马赫数为超声速,或者环境压强较低时,侧向力大小与飞行参数无关。在低空亚声速流中,侧向力随飞行马赫数增加迅速减小,随环境压强降低而减小。The complex inner and outer flow-field of solid rocket motor（SRM） secondary hot gas injection vector nozzle is numerically investigated using three-dimensional average Reynolds N-S equations and the k-ε turbulent models. The interaction between free outer flow and internal flow of vector nozzle is investigated. The results show that the flight parameters causes the change of pressure round the nozzle exit and affects the internal flow characteristics of the vector nozzle by means of the action of nozzle boundary layer. The side force has no connection with the flight status parameters when the flight Mach number is supersonic or the back pressure is lesser. On the low attitude and subsonic flow, the side force is reduced rapidly with the increasing of the flight Mach number and depressing of the back pressure.

关 键 词：固体火箭发动机 喷管气流 二次喷射 飞行参数 侧向力 主/次流干扰 数值仿真 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]