本文根據Von-Karman幾何大變形假設和含剪力應變之簡化板理論，推導一72個自由度的高階三角形板元素，用來分析與探討複合層板在承受溫度場改變的熱挫屈後行為。文中層板之側向位移分別由彎矩撓曲及剪力變形疊加之和。當層板溫度高於臨界挫屈溫度時，複合層板進入熱應力後挫屈階段，幾何大變形引入非線性勁度矩陣，此時的非線性平衡方程式由Newton-Raphson 解法求解。結果顯示，複合層板的幾何形狀如長寬比、纖維角度、曡層順序、材料性質及溫度分佈等，對熱挫屈後行為均有重大的影響。

Base on Von-Karman large deformation assumption and a simplified high order shear deformation plate theory, a 72 degree-of-freedom high precision high order triangular plate element is developed for the thermal post-buckling analysis of composite laminate plates subjected to temperature changes. The total transverse displacement of the laminate plate is expressed as the sum of the displacement due to bending and that due to shear deformation. When temperature reaches critical buckling temperature, the laminate plate goes into post-buckling region. The nonlinear system equation is solved by Newton-Raphson method. Numerical results show that the important of plate geometry, fiber orientation, stacking sequence, material properties, and temperature distribution effect on the thermal post-buckling behavior of composite laminate plates.

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