TY - JOUR
T1 - Fatigue Delamination Crack Growth in GFRP Composite Laminates
T2 - Mathematical Modelling and FE Simulation
AU - Ijaz, Hassan
AU - Saleem, Waqas
AU - Zain-ul-abdein, Muhammad
AU - Taimoor, Aqeel Ahmad
AU - Bin Mahfouz, Abdullah Salmeen
N1 - This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
PY - 2018/3/28
Y1 - 2018/3/28
N2 - Glass fibre-reinforced plastic (GFRP) composite laminates are used in many industries due to their excellent mechanical and thermal properties. However, these materials are prone to the initiation and propagation of delamination crack growth between different plies forming the laminate. The crack propagation may ultimately result in the failure of GFRP laminates as structural parts. In this research, a comprehensive mathematical model is presented to study the delamination crack growth in GFRP composite laminates under fatigue loading. A classical static damage model proposed by Allix and Ladevèze is modified as a fatigue damage model. Subsequently, the model is implemented in commercial finite element software via UMAT subroutine. The results obtained by the finite element simulations verify the experimental findings of Kenane and Benzeggagh for the fatigue crack growth in GFRP composite laminates.
AB - Glass fibre-reinforced plastic (GFRP) composite laminates are used in many industries due to their excellent mechanical and thermal properties. However, these materials are prone to the initiation and propagation of delamination crack growth between different plies forming the laminate. The crack propagation may ultimately result in the failure of GFRP laminates as structural parts. In this research, a comprehensive mathematical model is presented to study the delamination crack growth in GFRP composite laminates under fatigue loading. A classical static damage model proposed by Allix and Ladevèze is modified as a fatigue damage model. Subsequently, the model is implemented in commercial finite element software via UMAT subroutine. The results obtained by the finite element simulations verify the experimental findings of Kenane and Benzeggagh for the fatigue crack growth in GFRP composite laminates.
UR - https://doi.org/10.1155/2018/2081785
U2 - 10.1155/2018/2081785
DO - 10.1155/2018/2081785
M3 - Article
SN - 1687-5974
SN - 1687-5974
VL - 2018
JO - International Journal of Aerospace Engineering
JF - International Journal of Aerospace Engineering
M1 - 2081785
ER -