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In recent years, laminated composites are fairly utilized in marine, automotive, aerospace, military and other engineering
applications because of their high specific modulus (ratio between the young modulus and the density) and high specific
strength (ratio between strength and density). In addition to these features, fiber reinforced composites have inherent
tailorability such as fiber orientation and stacking sequence and provide great possibilities to designers against isotropic
materials. Generally, fail occurs four ways in structure: overstressing (strength critical structure), over deflection (stiffness
critical structure), resonant vibration, and buckling. In this regard, determination of the buckling load capacity of a
laminated composite plate under in-plane compressive loads is crucial for the design of composite structures.
The main aim of the study is to investigate the anti-buckling behavior of 64-layered graphite/epoxy laminated composite
plates for various aspect ratios and load ratios.
International Symposium on Light Alloys and Composite Materials
UHAKS
Mehmet Akçair
Melih Savran
Levent Aydın
Ozan Ayakdaş
Savaş Öztürk
Nilay Küçükdoğan