Effects of geometric parameters on failure behavior in laminated composite plates with two parallel pin-loaded holes

2008 ◽  
Vol 85 (1) ◽  
pp. 1-9 ◽  
Author(s):  
Ramazan Karakuzu ◽  
Numan Taylak ◽  
Bülent Murat İçten ◽  
Mehmet Aktaş
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Geometric Parameters ◽  
Failure Behavior ◽  
Laminated Composite Plates

Failure behavior of laminated composite plates with two serial pin-loaded holes

2008 ◽  
Vol 82 (2) ◽  
pp. 225-234 ◽  
Author(s):  
Ramazan Karakuzu ◽  
Cihan Rıza Çalışkan ◽  
Mehmet Aktaş ◽  
Bülent Murat İçten
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Failure Behavior ◽  
Laminated Composite Plates

Failure Behavior of Two Parallel Pinned/Bolted Composite Joints

2011 ◽  
Vol 27 (1) ◽  
pp. 121-127
Author(s):  
M. Pakdil ◽  
F. Sen ◽  
A. Cakan
Keyword(s):  
Glass Fibers ◽  
Laminated Composite ◽  
Composite Plates ◽  
Diameter Ratio ◽  
Laminated Plates ◽  
Hole Diameter ◽  
Failure Behavior ◽  
Geometrical Parameters ◽  
Composite Joints ◽  
Laminated Composite Plates

ABSTRACTIn this study, the failure behavior of two parallel pinned/bolted composite joints was investigated, experimentally. The laminated composite plates were produced from glass fibers and epoxy matrix. During the tests, various joint geometries and ply orientations were considered to decide the optimum joint geometry and suitable stacking sequence of the laminated composite plates for two parallel pinned/bolted joints. For these reasons, the distance from the free edge of the plate to hole diameter ratio (E/D) was changed from 1 to 5, the distance between two parallel holes to hole diameter ratio (K/D) was selected as 2 and 5, the distance from the lateral edge of the plate to hole diameter ratio (N/D) was taken as 2 and 3. The laminated plates were composed from 8 laminas to stuck onto together with three different orientations as [0°2 / 30°2]s, [0°2 / 45°2]s and [0°2 / 60°2]s. The experiments involved both pinned and bolted joint. Experimental results indicate that failure behaviors of pinned/bolted composite joints are strictly influenced from both orientations of laminated plates and geometrical parameters.

Ballistic performance of composite structure configurations with high elongation calendered rubber layer laminated to AA5083-H112 aluminum alloy

2021 ◽  
pp. 146442072110145
Author(s):  
Hasan Kasım
Keyword(s):  
Adhesion Strength ◽  
Laminated Composite ◽  
Composite Plates ◽  
Front Face ◽  
Laminated Composite Plates ◽  
Ballistic Performance ◽  
Rubber Layer ◽  
Interface Interaction ◽  
Metal Rubber ◽  
High Elongation

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.

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

2010 ◽  
Vol 19 (4) ◽  
pp. 096369351001900 ◽  
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.

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