Numerical and Experimental Investigation of Mechanical and Thermal Buckling Loads of Composite Laminated Plates | ||
| Engineering and Technology Journal | ||
| Article 1, Volume 29, Issue 9, June 2011, Pages 1830-1844 PDF (1.81 M) | ||
| DOI: 10.30684/etj.29.9.17 | ||
| Authors | ||
| Ammar A. Hussein; Hassan H. Mahdi; Nessren H. Ahmed | ||
| Abstract | ||
| In this study, the effect of temperature, aspect ratio, number of layer and boundary conditions on critical buckling load of composite laminated plate is investigated experimentally and numerically. Simply-Simply-Free-Free and Clamp-Clamp-Free-Free boundary conditions, three temperatures (40°C, 60°C and 80°C) and four aspect ratio (1, 1.3, 1.5 and 2) will consider for the experimental work. The thickness of the plate was changed by increasing the number of layer. It can be seen that when the temperature changes from 40°C to 80°C the maximum value of Pcr is about (225 N/mm) at (T = 40°C, a/b = 2 and NL = 4), the minimum value of Pcr is about (11.70 N/mm) at (T = 80°C, a/b = 1 and NL = 2). Also, it can be shown that in the case of symmetric cross ply laminate (0o/90o/0o) when the thermal load increased by about 100 % the buckling load decrease by about 50 % at aspect ratio equal to 1. Finally, It is shown that the critical buckling load increases with increasing the aspect ratio at constant temperature, number of layers and boundary conditions. | ||
| Keywords | ||
| composite plate; Thermal buckling; Finite element method | ||
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