Panel flutter analysis of general laminated composite plates

This study aims to determine the ballistic performances of laminated composite plates produced with AA5083-H112 series aluminum and rubber material with high elongation capacity under impact loading. To investigate the effect of rubber compounds, two types of rubber with calendered and damping were prepared. Thanks to the surface treatment applied to the aluminum plates, the rubber–metal adhesion strength was adjusted, and four different laminated composite plate samples were prepared. Calendered rubber was used on the bullet impact surface of all samples, and damping rubber was used on the back. It has been observed that the pressure barrier created by the calendered rubber bullet on the front face provides high performance to absorb energy. A detailed study was carried out on the total thickness of laminated composite plates, the interface adhesion strength between rubber and aluminum layers, and the ballistic performance of aluminum-rubber combinations. It was concluded that the laminated composite plate’s energy absorption would increase, especially by increasing the thickness of the dumping rubber layer on the back of the aluminum sheets. In the strong metal-rubber interface interaction between the rubber and aluminum layer, the bullet is stopped before the pressure barrier is formed. The penetration depth and bulging height increase, and most of the energy are transmitted through the aluminum plate. In the weak metal-rubber interface interaction, a significant portion of the energy is absorbed by the rubber and air thanks to the pressure barrier.

Download Full-text

Geometrically nonlinear analysis of laminated composite plates using RBF-PS meshless method

Composite Structures ◽

10.1016/j.compstruct.2021.113830 ◽

2021 ◽

pp. 113830

Author(s):

C.M. C. Roque ◽

J.Grasa

Keyword(s):

Nonlinear Analysis ◽

Meshless Method ◽

Laminated Composite ◽

Composite Plates ◽

Geometrically Nonlinear ◽

Laminated Composite Plates ◽

Geometrically Nonlinear Analysis

Download Full-text

Experimental and Numerical Buckling Analyses of Laminated Composite Plates under Temperature Effects

Advanced Composites Letters ◽

10.1177/096369351001900402 ◽

2010 ◽

Vol 19 (4) ◽

pp. 096369351001900 ◽

Cited By ~ 4

Author(s):

Emin Ergun

Keyword(s):

Composite Plate ◽

Numerical Solutions ◽

Laminated Composite ◽

Composite Plates ◽

Buckling Load ◽

Fibre Reinforcement ◽

Stacking Sequence ◽

Laminated Composite Plates ◽

Different Temperatures ◽

Good Agreement

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.

Download Full-text