摘要
采用顺序间接耦合的方法,针对某固体火箭发动机所使用的燃气舵,开展了偏转角度分别为0°、30°、45°的热分析数值研究。计算结果表明:偏转角度为0°、30°、45°时最大温度位置都出现在燃气舵前端;燃气在舵面上发生分离的区域主要是型面角度变化陡峭处,随着偏转角度的改变,分离点对温度影响程度也不同;偏转角的改变造成对附近流场的干扰程度增加,造成燃气在舵面上分离区域的改变,导致燃气舵侧面温度分布发生变化。
The numerical thermal analysis of gas vane, with different deflection angles, on a certain solid rocket motor was carried out using sequence indirect coupling method. The computational results showed that： the maximum temperature zone occurred in the front leading edge of gas vane when the deflection angle was 0° , 30° and 45° respectively the gas separation zone occurred in the abrupt transition location of gas vane the influence of gas separation zone was deferent according to the deflection angle variation of the deflection angle of gas vane disturbed the flow field near the gas vane and modified the gas separate zone which induced the transformation of the surface temperature distribution on the side of gas van.
出处
《弹箭与制导学报》
CSCD
北大核心
2007年第3期165-168,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
