Open AccessFEA of Circular Embedded Delamination with Variations in Temperature in a Composite Laminate using VCCT
Author(s) -
K. S. Vishwanath
Publication year - 2021
Publication title -
international journal for research in applied science and engineering technology
Language(s) - English
Resource type - Journals
ISSN - 2321-9653
DOI - 10.22214/ijraset.2021.36122
Subject(s) - delamination (geology) , materials science , composite material , composite number , buckling , structural engineering , finite element method , strain energy release rate , composite laminates , fibre reinforced plastic , shell (structure) , transverse plane , fracture mechanics , engineering , paleontology , tectonics , subduction , biology
The FRP laminates are widely implemented in aviation industry due to its advantages and applications other materials in terms of strength to weight ratio, design features and many more. The strength of the interface compared to longitudinal and lateral directions of the plies are comparatively less and give rise too poor transverse direction strength. Hence a failure mechanism called delamination will occur in case when tools are dropped or due to poor manufacturing which would give rise to interface delamination. In this paper, VCCT is employed at the interface between base and sub laminate to investigate for a circular shape delamination geometry of 60mm buckling driven delamination growth with variations in temperature for -20C, room temperature, 523C, 773C and 1273C. The computational prediction of delamination growth initiation is obtained by solving a CFRP specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the required energy release rate versus inplane strains and inplane loads versus compressive strains.