带燃气舵的固体火箭发动机尾流仿真  

Numerical Analysis of Plume Field for SRM with Gas Vane

作　　者：莫展[1] 白涛涛[1] 郭颜红[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《弹箭与制导学报》2011年第2期120-122,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：燃气舵的扰动使得固体火箭发动机高度欠膨胀的尾流场显得更加复杂。文中采用数值仿真计算的方法对比研究了不同高度下相同自由来流马赫数时的带燃气舵发动机尾流场的特性。得到存在燃气舵扰动时固体火箭发动机高度欠膨胀尾流场的轴向截面呈十字状;并且随着高度的增加尾流场膨胀程度增加,温度边界向外扩展;同时得到尾流场的长度约为200倍的发动机喷管出口直径。The plume field of solid rocket motor （SRM） with gas vane is much more complex than the one without the gas vane. The plume fields at the different altitude with the same free stream Mach number were compared by numerical simulation. The axis section of the SRM＇s plume field with gas vane is cross-shaped. The plume field and temperature boundary expands with the altitude increase. The length of the plume field is about 200 fold of nozzle＇s outlet diameter

关 键 词：固体火箭发动机 燃气舵 尾流场 数值仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]