摘要
风挡玻璃电防冰和除冰装置、飞机机翼及直升机旋翼电除冰装量都是有内加热的多层壁。这些多层壁中温度分布计算不仅在这些装置的设计计算中是必需的，而且在考虑多层壁的热变形及热应力时也是必要的。本文用数值法对有内加热的多层壁温度分布进行了研究，根据导热微分方程及各种边界条件，用克兰克－尼可尔辛法推出了典型结构的有限差表示式，然后用高斯－赛德迭代法求解线性方程组，得到了可用于多层壁瞬态温度分布的计算软件。本文用该软件对实际的多层金属壁及多层玻璃作了计算。计算表明，计算结果与文［３—５］所得结果相符。本文所述的方法可推广到二维及三维瞬态多层壁温度分布计算，也可用于无内加热层的多层壁温度计算。
There are multiple layer-walls with internal heater in glass de-icing and de-fogging for windshield or electric de-icing for aircraft wing and rotor. The calculation of transient temperautre distribution is not only necessary for de-icing design,but also necessary for consideration of thermal deformation and thermal stress. In this paper, temperature distribution for multiple layer-walls with internal heater is studied with numerical method.Based on conductive differential equations and bouudardary conditions,the Crank-Nicolson method is used to derive finite difference equations for typical nodes. The Gauss-Seidel iterative method is used to resolve the linear equations. Then,the computer program is obtained to calculate the transient temperature distribution for multiple layer-walls. This program can be also used to calculate the temperauture distribution of multiple layer-walls as well as multiple glass of windshield. The calculation results are in agreement with those obtained from Refs[3-5].The method of this paper can be extended to 2-dimensional or 3dimensional transient temperature calculation of composite bodies with or without internal heater.
出处
《南京航空航天大学学报》
CAS
CSCD
1994年第3期412-417,共6页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
热分析
温度分布
飞机
防水系统
thermal analysis
temperature distribution
finite difference method
aircraft ice protection
