飞行弹丸表面温度的两种数值计算方法

Two numerical methods to calculate surface temperature of flying projectile

为了预测弹丸在飞行过程的红外辐射特性,建立了飞行弹丸在气动热、内热源及太阳热辐射综合效应下的表面温度场模型。采用两种数值计算方法求解其表面温度特征,其中:运用Gauss-Seidel法获得了不同速度下的瞬态温度分布;运用Runge-Kutta法计算并分析了弹体壁厚、太阳热辐射以及内热源的热传导对其表面动态温度场的影响规律。结果表明:瞬态温度梯度随速度增加而非线性增加;壁厚越薄,越靠近弹头部,峰值温度和温度变化率越大;内热源的考虑方法对其表面动态温度场有较大影响,而太阳热辐射的影响较小。

To predict the infrared radiation characteristics of the projectile during flight,the temperature field model of flying projectile is established under the comprehensive effect of aerodynamic heating,internal heat source and the solar radiation.Two numerical methods are used to solve the surface temperature property.The Gauss-Seidel method is used to solve the transient temperature distribution under the different velocities.The Runge-Kutta method is used to calculate and analyze the surface dynamic temperature field affected by the wall thickness of the projectile body,internal heat source and solar radiation.The results show that the transient temperature gradient does not change with its velocity linearly.The thinner the wall thickness is,and the closer to the forehead,the higher the peak temperature and the rate are.The considering method of the heat source has great effect on its surface dynamic temperature field,but the impact of the solar radiation is less.