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为对含有电热防冰系统的机翼复合材料蒙皮层温度分布进行数值分析,采用欧拉法计算了机翼外表面水滴局部收集系数,采用边界层积分法计算了表面对流换热系数。建立了含内热源的三维各向异性导热模型,采用控制容积积分法推导出物体坐标系下的全隐离散方程。计算得到了防冰表面温度曲线,与相关文献中的实验结果有较好的一致,计算对比复合材料采用不同铺层方向时的结构温度场。计算表明,纤维方向沿翼弦方向时,利于热量在翼弦方向扩散,温度分布较为均匀。
In order to numerically analyze the temperature distribution of wing composite skin with electric anti-icing system, the Euler method was used to calculate the local collection coefficient of water droplets on the outer surface of wing and the convective heat transfer coefficient was calculated by the boundary layer integral method. A three-dimensional anisotropic thermal model with internal heat source was established. The governing equation of integral volume method was used to derive the all-implicit dispersion equation in the object coordinate system. The temperature curve of anti-icing surface is calculated, which is in good agreement with the experimental results in related literatures. The structure temperature field of different composite materials in different ply directions is calculated and compared. The calculation shows that when the fiber direction is along the chord direction, the heat is diffused in the chord direction and the temperature distribution is more uniform.