Abstract
ABSTRACT
 Critical buckling temperature of angle-ply laminated plate is developed using a higher-order displacement field. This displacement field used by Mantari et al based on a constant ‘‘m’’, which is determined to give results closest to the three dimensions elasticity (3-D) theory. Equations of motion based on higher-order theory angle ply plates are derived through Hamilton, s principle, and solved using Navier-type solution to obtain critical buckling temperature for simply supported laminated plates. Changing (α2/ α1) ratios, number of layers, aspect ratios, E1/E2 ratios for thick and thin plates and their effect on thermal buckling of angle-ply laminates are studied in detail. It is concluded that, this displacement field produces numerical results close to 3-D elasticity theory with maximum discrepancy (7.4 %).
Highlights
Laminated composite plates are used widely in aeronautical, marine and mechanical industries as well as in other fields of modern engineering structures, those structure are often subjected to thermal load especially aircraft, launch vehicle and missiles structures, which may cause buckling of structure with certain boundary conditions, there are many investigations about thermal buckling. Thangaratnam, 1989. used finite element method using semiloof elements to analyze critical buckling temperature for composite laminates under thermal load
Multi parameter-reduction method based on a first-order shear deformation theory, in connection with mixed finite-element is developed to study the effect of different lamination and material parameters on stability of the plate
Critical temperature of supported composite plate is obtained using high order shear deformation theory of plate based on displacement field used by Mantari et al, 2011 Effect of many thin and thick plate parameters, such as aspect ratio, E1/E2 ratio, α2/ α1 ratio for antisymmetric angle ply are investigated
Summary
Laminated composite plates are used widely in aeronautical, marine and mechanical industries as well as in other fields of modern engineering structures , those structure are often subjected to thermal load especially aircraft, launch vehicle and missiles structures, which may cause buckling of structure with certain boundary conditions, there are many investigations about thermal buckling. Thangaratnam, 1989. used finite element method using semiloof elements to analyze critical buckling temperature for composite laminates under thermal load. Studied thermal buckling of antisymmetric angle-ply laminated supported subjected to uniform thermal load using higher order deformation theory which account for transverse shear and transverse normal strain to obtain exact-closed form solution. Prabhut and Dhanaraj, 1994, analyzed thermal buckling of symmetric cross-ply and antisymmetric angle-ply laminated composite plates subjected to uniform temperature distribution using finite element method which based on the first order shear deformation theory. Critical temperature of supported composite plate is obtained using high order shear deformation theory of plate based on displacement field used by Mantari et al , 2011 Effect of many thin and thick plate parameters, such as aspect ratio, E1/E2 ratio, α2/ α1 ratio for antisymmetric angle ply are investigated
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