Free vibration and stability of angle-ply laminated composite and sandwich plates under thermal loading |
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| Affiliation: | 1. Department of Mechanical Engineering, University of Guilan, P.O. Box 3756, Rasht, Iran;2. School of Civil and Environmental Engineering, Georgia Institute of Technology, Atlanta, GA 30332, USA;1. School of Civil & Environmental Engineering, The University of New South Wales, Sydney, Australia;2. Department of Civil Engineering, Indian Institute of Technology, Bombay, India;3. Stress & DTA, IES-Aerospace, Mahindra Satyam Computer Services Ltd., Bangalore, India;4. Henri Tudor Research Center, 29JFK, Avenue John F Kennedy, L-195 Luxembourg, Luxembourg;1. Department of Mechanical Engineering, Faculty of Engineering, Imam Khomeini International University, Qazvin, Iran;2. Department of Mechanical Engineering, Nitte Meenakshi Institute of Technology, Yelahanka, Bangalore, India;1. Department of Architecture and Civil Engineering, City University of Hong Kong, Kowloon, Hong Kong;2. College of Information Science and Technology, Shanghai Ocean University, Shanghai 201306, China;1. Department of Mechanical Engineering, National Institute of Technology Rourkela, Odisha 769008, India;2. Production Engineering Department, Veer Surendra Sai University of Technology, Burla, Sambalpur, Odisha 768018, India |
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| Abstract: | A two-dimensional global higher-order deformation theory is presented for the free vibration and stability problems of angle-ply laminated composite and sandwich plates subjected to thermal loading. By using the method of power series expansion of continuous displacement components, a set of fundamental governing equations which can take into account the effects of both transverse shear and normal stresses is derived through Hamilton’s principle. Several sets of truncated Mth order approximate theories are applied to solve the eigenvalue problems of a simply supported angle-ply multilayered plate. Natural frequencies and critical temperatures of angle-ply laminated composite and sandwich plates subjected to thermal loading are obtained. Critical temperatures are obtained by increasing the temperature until the natural frequency vanishes. The effects of prebuckling displacements on the natural frequencies and critical temperatures are taken into account. Modal displacement distributions through the transverse direction of the laminates are plotted for the specific temperature parameter. Numerical results are compared with those of the published existing theories. The present global higher-order approximate theories can predict the natural frequencies and critical temperatures of angle-ply laminated composite and sandwich plates subjected to thermal loading accurately within small number of unknowns. |
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