Abstract
In this study, the thermal buckling behavior of composite laminate plates cross-ply and angle-ply all edged simply supported subjected to a uniform temperature field is investigated, using a simple trigonometric shear deformation theory. Four unknown variables are involved in the theory, and satisfied the zero traction boundary condition on the surface without using shear correction factors, Hamilton's principle is used to derive equations of motion depending on a Simple Four Variable Plate Theory for cross-ply and angle-ply, and then solved through Navier's double trigonometric sequence, to obtain critical buckling temperature for laminated composite plates. Effect of changing some design parameters such as, orthotropy ratio (E1/E2), aspect ratio (a/b), thickness ratio (a/h), thermal expansion coefficient ratio (α2/α1), are investigated, which have the same behavior and good agreement when compared with previously published results with maximum discrepancy (0.5%).
Highlights
Thermal buckling research is critical for structural components used in high-speed aircraft, rockets, and space vehicles, where thermal loads are caused by aerodynamic and solar radiation heating, as well as for nuclear reactors and chemical planets, which are typically subjected to an elevated temperature regime during their service lives, (Cetkovic, 2016), (Shen, 2013), concerned thermal buckling and post-buckling behavior which presented for fiberreinforced laminated plates subjected to in-plane temperature variation and resting on an elastic foundation, The governing equations are based on a higher order shear deformation plate theory that includes plate–foundation interaction and the thermal effect (Mansouri and Shariyat, 2014)
The refined four parameters plate theory (RPT) needs less displacement parameters and is usually more accurate than the pth order generalization of theory of Reddy (GRT), both are less accurate than the third order five parameters of Reddy theory (TOST). (Shaterzadeh, Abolghasemi and Rezaei, 2014) studied thermal buckling analysis of symmetric and antisymmetric laminated composite plates with a cut-out, subjected to a uniform temperature rise for different boundary conditions, The stiffness matrices and thermal force vector are derived according to first-order shear deformation theory (FSDT). (Ounis, Tati and Benchabane, 2014) focused on the classical plate theory, and investigated the thermal buckling behavior of composite laminated plates under uniform temperature distribution
The present finite element is a combination of a linear isoparametric membrane element and a high precision rectangular Hermitian element. (Vosoughi and Nikoo, 2015) developed a hybrid method for maximizing fundamental natural frequency and thermal buckling temperature of laminated composite plates that is a new combination of the differential quadrature method (DQM) based on the first-order shear deformation theory (FSDT) of plates and are discretized using the (DQM)
Summary
Thermal buckling research is critical for structural components used in high-speed aircraft, rockets, and space vehicles, where thermal loads are caused by aerodynamic and solar radiation heating, as well as for nuclear reactors and chemical planets, which are typically subjected to an elevated temperature regime during their service lives, (Cetkovic, 2016),. (Manickam et al, 2018) used a finite element approach based on first-order shear deformation theory, investigated the thermal buckling behavior of variable stiffness laminated composite plates subjected to thermal loads. (Sadiq and Majeed, 2019) using a higher-order displacement field, Mantari et al determined the critical buckling temperature of an angle-ply laminated plate This displacement field is based on a constant "m" chosen to generate results consistent with three-dimensional elasticity (3-D) theory. (Alabas and Majid, 2020) and based on classical laminated plate theory, used the improved Rayleigh-Ritz method and Fourier series to evaluate the thermal buckling behavior of laminated composite thin plates with a general elastic boundary condition applied to an in-plane uniform temperature distribution (CLPT). The efficiency of a four-variable refined trigonometric shear deformation theory for thermal buckling analysis of cross-ply and angle-ply laminated composite plates is investigated.
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
