Thermal Buckling and Post-Buckling of Laminated Composite Plates with SMA Fibers using Layerwise Theory

2009 ◽  
Vol 10 (6) ◽  
pp. 423-429 ◽  
Author(s):  
C. Naveen Kumar ◽  
B. N. Singh
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Laminated Composite Plates ◽  
Layerwise Theory ◽  
Post Buckling

scholarly journals Thermal Buckling and Post-Buckling Improvements of Laminated Composite Plates Using Finite Element Method

2011 ◽  
Vol 471-472 ◽  
pp. 536-541 ◽  
Author(s):  
Zainudin A. Rasid ◽  
Ayob Amran ◽  
Rizal Zahari ◽  
Faizal Mustapha ◽  
D.L. Majid ◽  
...  
Keyword(s):  
Finite Element ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Element Formulation ◽  
Laminated Composite Plates ◽  
Aerospace Applications ◽  
Post Buckling

Thermal buckling and thermal post-buckling behaviours of laminated composite plates are improved by embedding shape memory alloy wires within laminates of composite plates. The procedure is to use the recovery stress that is induced when the reverse transformation of the shape memory alloy from martensite to austenite phases is constrained. For aerospace applications where the source of the shape memory alloy heating is the high temperature environment itself, a study is conducted to see the effect of shape memory alloy in improving the thermal buckling and post-buckling of composite plates. Due to the temperature dependent nature of the composite matrix and the shape memory alloy, the finite element formulation developed here is in the incremental form. Solving this non-linear model using the developed in-house source code, critical loads are determined and the post-buckling paths of the shape memory alloy composite plates are traced. This study shows that by embedding the shape memory alloy within composite plates, the thermal buckling and post-buckling behaviours of composite plates can be improved substantially.

Bending of Laminated Composite Plates

2015 ◽  
Vol 725-726 ◽  
pp. 667-673 ◽  
Author(s):  
Marina Rakočević ◽  
Nikolay Vatin
Keyword(s):  
Cross Section ◽  
Numerical Models ◽  
Single Layer ◽  
Laminated Composite ◽  
Composite Plates ◽  
Layered Composite ◽  
Laminated Composite Plates ◽  
Layerwise Theory ◽  
Geometrical Characteristics ◽  
Laminate Theory

In this work, there are presented overviews of theoretical and numerical models for defining the stress-strain state in the cross section of moderately thick and thick composite plates in case of bending. Layered composite plates are constructed by combination of layers of various materials and geometrical characteristics, wherein each of them has got a bearing capacity in previously defined directions. By applying Equivalent Single-layer Laminate Theory (or ESL theory) these layers' problems cannot be solved successfully. That is the reason to apply contemporary theories of plates, in literature known as Layerwise theories. At the end of this work, there are given numeric examples of applying Partial Layerwise Theory.

scholarly journals Non-linear analysis on stability of corrugated cross-ply laminated composite plates

2006 ◽  
Vol 28 (4) ◽  
pp. 197-206
Author(s):  
Dao Huy Bich ◽  
Khuc Van Phu
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Sine Wave ◽  
Laminated Composite Plates ◽  
Non Linear ◽  
Post Buckling ◽  
Corrugated Plates ◽  
The Stability ◽  
Analytical Expressions ◽  
Linear Stability Problem

In the present paper the governing equations for corrugated cross-ply laminated composite plates in the form of a sine wave are developed based on the Kirchoff-Love's theory and the extension of Seydel's technique. By using Bubnov-Galerkin method approximated analytical solutions to the non-linear stability problem of corrugated laminated composite plates subjected to biaxial loads are investigated. The post buckling load-deflection curve of corrugated plates and analytical expressions of the upper and lower buckling loads are presented. The effectiveness of corrugated plates in enhancing the stability compared with corresponding fiat plates is given.

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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