Fast analytical method describing the postbuckling behavior of long, symmetric, balanced laminated composite plates under biaxial compression and shear

2012 ◽  
Vol 94 (6) ◽  
pp. 2001-2009 ◽  
Author(s):  
M. Beerhorst ◽  
M. Seibel ◽  
C. Mittelstedt
Keyword(s):  
Analytical Method ◽  
Laminated Composite ◽  
Composite Plates ◽  
Biaxial Compression ◽  
Laminated Composite Plates ◽  
Postbuckling Behavior

Natural Frequency of Laminated Composite Plates Using a Sinusoidal Theory

2014 ◽  
Vol 709 ◽  
pp. 148-152
Author(s):  
Guo Qing Zhou ◽  
Ji Wang ◽  
Song Xiang
Keyword(s):  
Differential Equations ◽  
Analytical Method ◽  
Deformation Theory ◽  
Natural Frequencies ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Simply Supported ◽  
Sinusoidal Shear Deformation Theory

Sinusoidal shear deformation theory is presented to analyze the natural frequencies of simply supported laminated composite plates. The governing differential equations based on sinusoidal theory are solved by a Navier-type analytical method. The present results are compared with the available published results which verify the accuracy of sinusoidal theory.

scholarly journals Optimization of Laminated Composite Plates for Maximum Biaxial Buckling Load

2020 ◽  
Vol 36 (2) ◽  
Author(s):  
Pham Dinh Nguyen ◽  
Quang-Viet Vu ◽  
George Papazafeiropoulos ◽  
Hoang Thi Thiem ◽  
Pham Minh Vuong ◽  
...  
Keyword(s):  
Fiber Orientation ◽  
Orientation Angle ◽  
Laminated Composite ◽  
Optimization Procedure ◽  
Composite Plates ◽  
Buckling Load ◽  
Biaxial Compression ◽  
Laminated Composite Plates ◽  
Design Variables ◽  
Fiber Orientation Angle

This paper proposes an optimization procedure for maximization of the biaxial buckling load of laminated composite plates using the gradient-based interior-point optimization algorithm. The fiber orientation angle and the thickness of each lamina are considered as continuous design variables of the problem. The effect of the number of layers, fiber orientation angles, thickness and length to thickness ratios on the buckling load of the laminated composite plates under biaxial compression is investigated. The effectiveness of the optimization procedure in this study is compared with previous works.

An analytical method for 3-D analysis of circular laminated composite plates

1996 ◽  
Vol 117 (1-4) ◽  
pp. 191-203
Author(s):  
X. Jiang ◽  
X. Zhang ◽  
B. Cheng
Keyword(s):  
Analytical Method ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Composite Plates

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

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.

Elastic Wave Propagation in Laminated Composite Plates

1991 ◽  
Vol 113 (4) ◽  
pp. 411-418 ◽  
Author(s):  
W. M. Karunasena ◽  
R. L. Bratton ◽  
S. K. Datta ◽  
A. H. Shah
Keyword(s):  
Analytical Method ◽  
Guided Waves ◽  
Laminated Composite ◽  
Composite Plates ◽  
Thickness Variation ◽  
Dispersion Characteristics ◽  
Laminated Plate ◽  
Laminated Composite Plates ◽  
Number Of Layers ◽  
Stiffness Method

A stiffness method and an analytical method have been used to study the dispersion characteristics of guided waves in laminated composite plates. Both cross-ply and angle-ply plates have been considered in the analysis. The objective of the study is to analyze the effect of fiber orientation, ply layout configuration, and number of layers on the dispersion characteristics. A Rayleigh-Ritz type of approximation of the through-thickness variation of the displacements that maintain continuity of displacements and tractions at the interfaces between the layers has been used in the stiffness method. The analytical method solves the exact dispersion relation of the laminated plate by using the Muller’s method with initial guesses obtained through the stiffness method. Both methods are applicable to plates with arbitrary number of layers having distinct mechanical properties. Numerical results presented show strong influence of anisotropy on the guided waves.

Failure Mechanisms of Notched Laminates Under Biaxial Compression at Elevated Temperature

2000 ◽  
Author(s):  
Junghyun Ahn ◽  
Anthony M. Waas
Keyword(s):  
Elevated Temperature ◽  
Failure Mechanisms ◽  
Compressive Loading ◽  
Stress Raiser ◽  
Laminated Composite ◽  
Composite Plates ◽  
Biaxial Compression ◽  
Laminated Composite Plates ◽  
Final Failure ◽  
Circular Cutout

Abstract A compression test at elevated temperature was performed to investigate the notch sensitivity and failure mechanisms of fibrous laminated composite plates containing a stress raiser, in the form of a circular cutout, under equi-biaxial and uniaxial compressive loading. Strains measured at various locations on the specimen surface and cutout edge were used to monitor the initiation of failure. Unloading the specimen before global failure made it possible to understand the failure mechanism associated with the final failure mode.

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