Effects of nonuniform boundary conditions on the buckling load optimization of laminated composite plates

The aim of this study is to investigate, experimentally and numerically, the change of critical buckling load in composite plates with different ply numbers, orientation angles, stacking sequences and boundary conditions as a function of temperature. Buckling specimens have been removed from the composite plate with glass-fibre reinforcement at [0°]i and [45°]i (i= number of ply). First, the mechanical properties of the composite material were determined at different temperatures, and after that, buckling experiments were done for those temperatures. Then, numerical solutions were obtained by modelling the specimens used in the experiment in the Ansys10 finite elements package software. The experimental and numerical results are in very good agreement with each other. It was found that the values of the buckling load at [0°] on the composite plates are higher than those of other angles. Besides, symmetrical and anti-symmetrical conditions were examined to see the effect of the stacking sequence on buckling and only numerical solutions were obtained. It is seen that the buckling load reaches the highest value when it is symmetrical in the cross-ply stacking sequence and it is anti-symmetrical in the angle-ply stacking sequence.

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Minimize the Deflection of Laminated Composite Plates under the External Load Using Fiber Orientation Angle

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.709.144 ◽

2014 ◽

Vol 709 ◽

pp. 144-147

Author(s):

Ying Tao Chen ◽

Song Xiang ◽

Wei Ping Zhao

Keyword(s):

Fiber Orientation ◽

External Load ◽

Optimization Problem ◽

Orientation Angle ◽

Laminated Composite ◽

Composite Plates ◽

Laminated Composite Plates ◽

Load Optimization ◽

Fiber Orientation Angle ◽

Optimization Parameters

Optimization of fiber orientation angle is studied to minimize the deflection of the laminated composite plates by the genetic algorithm. The objective function of optimization problem is the minimum deflection of laminated composite plates under the external load; optimization parameters are fiber orientation angle of laminated composite plates. The results for the optimal fiber orientation angle and the minimum deflection of the 4-layer plates are presented to demonstrate the validity of present method.

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Optimization of Laminated Composite Plates for Maximum Biaxial Buckling Load

VNU Journal of Science Mathematics - Physics ◽

10.25073/2588-1124/vnumap.4509 ◽

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.

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Structural Optimization of Laminated Composite Plates for Maximum Buckling Load Capacity Using Genetic Algorithm

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.348-349.725 ◽

2007 ◽

Vol 348-349 ◽

pp. 725-728 ◽

Cited By ~ 5

Author(s):

Omer Soykasap ◽

Şükrü Karakaya

Keyword(s):

Genetic Algorithm ◽

Structural Optimization ◽

Load Capacity ◽

Laminated Composite ◽

Global Solutions ◽

Composite Plates ◽

Buckling Load ◽

Laminated Composite Plates ◽

Static Loads ◽

Aspect Ratios

In this study, the structural optimization of laminated composite plates for maximum buckling load capacity is performed by using genetic algorithm. The composite plate under consideration is a 64-ply laminate made of graphite/epoxy, is simply supported on four sides, and subject to in-plane compressive static loads. The critical buckling loads are determined for several load cases and different plate aspect ratios using 2-ply stacks of 02, ±45, 902. The problem has multiple global solutions, the results of which are compared with previously published results.

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