On the buckling behavior of cross-ply laminated composite plates due to circular/elliptical cutouts

2006 ◽  
Vol 75 (1-4) ◽  
pp. 3-6 ◽  
Author(s):  
S.A.M. Ghannadpour ◽  
A. Najafi ◽  
B. Mohammadi
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Buckling Behavior

Hybridization effects on the buckling behavior of laminated composite plates

2014 ◽  
Vol 118 ◽  
pp. 19-27 ◽  
Author(s):  
Eyüp Yeter ◽  
Ahmet Erkliğ ◽  
Mehmet Bulut
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Buckling Behavior

scholarly journals Thermal Buckling of Laminated Composite Plates Using a Simple Four Variable Plate Theory

2021 ◽  
Vol 27 (9) ◽  
pp. 1-19
Author(s):  
Hussein Tawfeeq Yahea ◽  
Wedad Ibraheem Majeed
Keyword(s):  
Plate Theory ◽  
Equations Of Motion ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Design Parameters ◽  
Laminated Composite Plates ◽  
Buckling Behavior ◽  
Uniform Temperature Field

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%).

Relative Post-Buckling Stiffness Calculation of Symmetrically Laminated Composite Plates Using an Exact Finite Strip

2010 ◽  
Vol 123-125 ◽  
pp. 201-204 ◽  
Author(s):  
Seyyed Amir Mahdi Ghannadpour ◽  
Hamid Reza Ovesy
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Unknown Coefficient ◽  
Laminated Composite Plates ◽  
Total Strain Energy ◽  
Finite Strip ◽  
Finite Strip Method ◽  
Buckling Behavior ◽  
Out Of Plane ◽  
Post Buckling

This paper presents the theoretical developments of an exact finite strip for the buckling and initial post-buckling analyses of symmetrically laminated composite plates. The so-called exact finite strip is developed based on the concept that it is effectively a plate. The present method, which is designated by the name Full-analytical Finite Strip Method in this paper, provides an efficient and extremely accurate buckling solution. In the development process, the Von-Karman’s equilibrium equation is solved exactly to obtain the buckling loads and the corresponding form of out-of-plane buckling deflection modes. The investigation of thin flat plate buckling behavior is then extended to an initial post-buckling study with the assumption that the deflected form immediately after the buckling is the same as that obtained for the buckling. The post-buckling study is effectively a single-term analysis, which is attempted by utilizing the so-called semi-energy method. In this method, the Von-Karman’s compatibility equation governing the behavior of symmetrically laminated composite plates is used together with a consideration of the total strain energy of the plate. Through the solution of the compatibility equation, the in-plane displacement functions are developed in terms of the unknown coefficient in the assumed out-of-plane deflection function. These in-plane and out-of-plane deflected functions are then substituted in the total strain energy expressions and the theorem of minimum total potential energy is applied to solve for the unknown coefficient. The developed method is subsequently applied to analyze the initial post-buckling behavior of some representative thin flat plates for which the results are also obtained through the application of a semi-analytical finite strip method. Through the comparison of the results and the appropriate discussion, the knowledge of the level of capability of the developed method is significantly promoted.

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