POSTBUCKLING BEHAVIOR OF SKEW COMPOSITE PLATES

2012 ◽  
Vol 3 (2) ◽  
pp. 161-170 ◽  
Author(s):  
N. S. Azikov ◽  
Yu. V. Gaidarzhi
Keyword(s):  
Composite Plates ◽  
Postbuckling Behavior

Thermal postbuckling behavior of laminated composite plates

AIAA Journal ◽  
1994 ◽  
Vol 32 (6) ◽  
pp. 1336-1338 ◽  
Author(s):  
Gajbir Singh ◽  
G. Venkateswara Rao ◽  
N. G. R. lyengar
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Postbuckling Behavior ◽  
Thermal Postbuckling

scholarly journals Analysis and Design for the Moderately Deep Postbuckling Behavior of Composite Plates

2017 ◽  
Vol 54 (1) ◽  
pp. 327-335 ◽  
Author(s):  
Zhangming Wu ◽  
Gangadharan Raju ◽  
Paul Weaver
Keyword(s):  
Composite Plates ◽  
Postbuckling Behavior ◽  
Analysis And Design

Thermally induced postbuckling of thin CNT-reinforced composite plates under nonuniform in-plane temperature distributions

2020 ◽  
pp. 089270572096217
Author(s):  
Le Thi Nhu Trang ◽  
Hoang Van Tung
Keyword(s):  
Thermal Load ◽  
Effective Properties ◽  
Plate Theory ◽  
Composite Plates ◽  
Functionally Graded ◽  
Postbuckling Behavior ◽  
Classical Plate Theory ◽  
Temperature Distributions ◽  
Basic Equations ◽  
Plane Temperature

This paper presents an analytical investigation on postbuckling behavior of thin plates reinforced by carbon nanotubes (CNTs) and subjected to nonuniform thermal loads. Unlike many previous works considered ideal case of thermal load is that uniform temperature rise, the present study considers more practical situations of thermal load are that sinusoidal and linear in-plane temperature distributions. CNTs are reinforced into matrix through functionally graded distributions and effective properties of nanocomposite are estimated according to extended rule of mixture. Basic equations are based on classical plate theory taking into account Von Karman nonlinearity, initial geometrical imperfection, interactive pressure from elastic foundations and elasticity of tangential constraints of simply supported boundary edges. Basic equations are solved by using analytical solutions and Galerkin method. From the obtained closed-form relations, thermal buckling and postbuckling behavior of nanocomposite plates are analyzed through numerical examples.

Improved Secant Matrices for the Postbuckling Analysis of Thin Composite Plates

2003 ◽  
Vol 03 (03) ◽  
pp. 355-375 ◽  
Author(s):  
S. Arul Jayachandran ◽  
S. Gopalakrishnan ◽  
R. Narayanan
Keyword(s):  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Initial Imperfection ◽  
Composite Plates ◽  
Shear Stiffness ◽  
Laminated Composite Plates ◽  
Postbuckling Behavior ◽  
Initial Imperfections ◽  
First Order ◽  
Total Displacement

To study the postbuckling behavior of imperfect laminated composite plates, improved incremental or secant matrices are presented in this paper using what is called additional displacement formulation (ADF). These secant matrices are derived using the Marguerre's shell theory and they can be used in combination with any thin plate finite element. The advantage of the present formulation is that it involves no numerical approximation in forming the initial imperfection matrices as opposed to earlier secant matrices published in the literature using total displacement formulation. With the addition of shear stiffness matrix and little modification, the present incremental matrices could be extended to model postbuckling behavior of plates using the first-order shear deformation theory. The secant matrices presented in this study are shown to be very accurate in tracing the postbuckling behavior of thin isotropic and laminated composite plates with general initial imperfections.

POSTBUCKLING ANALYSIS OF VARIABLE STIFFNESS COMPOSITE PLATES USING A FINITE ELEMENT-BASED PERTURBATION METHOD

2011 ◽  
Vol 11 (04) ◽  
pp. 735-753 ◽  
Author(s):  
T. RAHMAN ◽  
S. T. IJSSELMUIDEN ◽  
M. M. ABDALLA ◽  
E. L. JANSEN
Keyword(s):  
Finite Element ◽  
Perturbation Method ◽  
Composite Plates ◽  
Variable Stiffness ◽  
Reduced Order Model ◽  
Perturbation Approach ◽  
Postbuckling Behavior ◽  
Order Model ◽  
Fast Analysis ◽  
Reduced Order

Modern fiber placement machines allow laminates with spatially varying stiffness properties to be manufactured. In earlier research, the authors optimized variable stiffness plates for maximum buckling load, demonstrating significant improvements in load-carrying capacity. In aerospace applications, panel structures are often permitted to enter the postbuckling regime during service. It is, therefore, not only important to understand their postbuckling behavior, but also to develop fast analysis methods that can subsequently be used in a design optimization framework. The aim of the present research is to study the postbuckling behavior of the optimized plates using a perturbation method that has been developed earlier within a general-purpose finite element environment. The perturbation approach is used to compute postbuckling coefficients, which are used to make a quick estimate of the postbuckling stiffness of the panel and to establish a reduced-order model. In the present work, the postbuckling analysis of variable stiffness plates is carried out using the reduced-order model, and the potential of the approach for incorporation within the optimization process is demonstrated.

Postbuckling behavior of composite plates with through-the-width delaminations

2008 ◽  
Vol 46 (7-9) ◽  
pp. 939-946 ◽  
Author(s):  
M. Kharazi ◽  
H.R. Ovesy
Keyword(s):  
Composite Plates ◽  
Postbuckling Behavior
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