电热防冰过程中复合材料机翼传热数值分析  

Numerical Analysis of Heat Transfer for Composite Wing Skin During Aircraft Electrothermal Anti-icing Process

作　　者：毛杨础 苏向辉[1] MAO Yang-chu;SU Xiang-hui(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空宇航学院,江苏南京210016

出　　处：《航空计算技术》2017年第5期32-36,45,共6页Aeronautical Computing Technique

基　　金：江苏省高校优势学科建设工程基金项目资助

摘　　要：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。For numerical analysis of temperature distribution for composites wing skin layers containing electrothermal anti icing system,the water droplets local collection coefficient was calculated by theEuler′smethod,the surface convective heat transfer coefficient was calculated by a integral analysis of thermal boundary layers.A three dimensional heat transfer mathematical model with internal heat sources was presented,which considered the anisotropic of the heat conductivity coefficient.The full implicit discrete equations under the object coordinate system of the model was deduced by the control volume integral method.The temperature curve of the ice surface was predicted,and it had better agreement with the experimental results in the literature.The temperature field of the structure with different ply orientation of the composite materials was predicted to contrast.Theoretical calculations reveal that when the fiber direction along the chord direction,the heat diffusion in the chord direction is better,and the temperature distribution is more uniform.

关 键 词：电热防冰 复合材料机翼蒙皮 各向异性 数值分析 温度分布 

分 类 号：V244.15[航空宇航科学与技术—飞行器设计]