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Modeling of the dynamic delamination of L-shaped unidirectional laminated composites
Date
2012-03-01
Author
Gozluklu, Burak
Çöker, Demirkan
Metadata
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This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
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One of the widely used geometrically complex parts in advanced commercial aircraft is the L-shaped composite. Due to the sharp curved geometry, interlaminar opening stresses are induced and delamination occurs under considerable mode-mixities in L-shaped beams. Dynamic phenomena during delamination initiation and propagation of L-shaped beams are investigated using dynamic (explicit) finite element analysis in conjunction with cohesive zone methods. The 2-D model consists of 24 plies of unidirectional CFRP laminate with an initial 1 mm crack at the center of the laminate at the bend. Loading is applied parallel to one of the arms quasi-statically. The loading type yields different traction fields and mode-mixities in the two sides of the crack in which delamination occurs under shear stress dominated loading on one crack tip and opening stress dominated loading on the other. The speed of the delamination under shear dominated loading at one side is 800 m/s and under normal stress dominated loading is 50 m/s. In addition radial compressive waves at the interface are observed. Finally, as the thickness is changed, a different failure mode is observed in which a secondary crack nucleates at the arm and propagates towards the center crack.
Subject Keywords
Delamination
,
Cohesive zone method
,
Finite element analysis
,
Composite mechanics
,
Fracture mechanics
,
Curved laminate
URI
https://hdl.handle.net/11511/41721
Journal
COMPOSITE STRUCTURES
DOI
https://doi.org/10.1016/j.compstruct.2011.11.015
Collections
Department of Aerospace Engineering, Article