An Investigation of Square Delamination Effects on the Buckling Behavior of Laminated Composite Plates with a Square Hole by using Three-dimensional FEM Analysis

2005 ◽  
Vol 24 (11) ◽  
pp. 1119-1130 ◽  
Author(s):  
Mehmet Zor ◽  
Faruk Sen ◽  
M. Evren Toygar
Keyword(s):  
Three Dimensional ◽  
Laminated Composite ◽  
Fem Analysis ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Buckling Behavior ◽  
Square Hole

Shape Optimization of Cutouts in Laminated Composite Plates Using Solid Element

2005 ◽  
Vol 297-300 ◽  
pp. 2740-2745
Author(s):  
Seok Yoon Han ◽  
Y.J. Ma ◽  
J.Y. Park
Keyword(s):  
Shape Optimization ◽  
Three Dimensional ◽  
Laminated Composite ◽  
Composite Plates ◽  
Volume Control ◽  
Growth Strain ◽  
Laminated Composite Plates ◽  
Failure Index ◽  
Solid Element ◽  
Strain Method

Shape optimization was performed to obtain the precise shape of cutouts including the internal shape of cutouts in laminated composite plates by three dimensional modeling using solid element. The volume control of the growth-strain method was implemented and the distributed parameter was chosen as Tsai-Hill failure index for shape optimization. In order to verify the validity of the obtained optimal shapes, the changes of the maximum Tsai-Hill failure index were examined for each load condition and cutouts. The following conclusions were obtained in this study; 1) It was found that growth-strain method was applied efficiently to shape optimization of three dimensional cutouts in anisotropic laminate composite, 2) The optimal three dimensional shapes of the various load conditions and cutouts were obtained, 3) The maximum Tsai-Hill failure index was reduced up to 68% when shape optimization was performed under the initial volume by volume control of growth-strain method.

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%).

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