| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 91 === Subject ：Thermal Buckling Analysis Of Composite Laminates
Student ：Cheng-Yuan Chen
Adviser ：Le-Chung Shiau
In this thesis, by using the first order shear deformation plate theory, a 36 degree-of-freedom high precision, high order triangular plate element we are going to study the thermal buckling behave of angle ply and cross ply composite laminate with shear deformation analysis of composite plates under a uniformly distributed temperature field. Since the sequence of lamina is different, there may be error in bending stiffness both in the direction of x and y, which would seriously change the buckling mode and critical temperature. In this study, a simply supported cross ply laminate with various sequences are considered, and we are going to investigate relation between aspect ratio and the buckling mode and critical temperature. Besides, we would also focus on the bucking mode and critical temperature of angle ply laminate under various sequences, aspect ratios and the fiber angles. The result shows that in the cross ply laminate, under different sequences and boundary conditions, the buckling mode and critical temperature would change with different aspect ratio. In cross ply laminate, under different sequences and boundary conditions, there is a close relationship between the aspect ratio, fiber angle, buckling mode and critical temperature.
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