In this research, dynamic progressive failure of Glass-Fiber-Reinforced aluminum laminates under low-energy impact was modelled. Intralaminar damage models, strain-based damage evolution laws, Puck failure criteria were used in ABAQUS-VUMAT software for modelling. Bilinear cohesive model was used for interface delamination, and the Johnson-Cook models were employed for aluminum layers. Damage evolution behaviours of this hybrid composite were calculated. After that, energy dissipation mechanisms were examined to identify the progressive failure and delamination of composite layers and plastic deformation of aluminum layers. In order to determine stress intensity at crack tip, the analytical model for constant-amplitude fatigue crack propagation according to Paris law was applied. Also, bridging stress along crack length in aluminum layer was investigated by correlation between the delamination growth rate and energy release rate in hybrid composite layers. The obtained findings indicated that the highest amount of peak low velocity impact force belonged to Glare 4 3/2. The presented numerical method based on bridging stress phenomena can successfully be used for predicting the post impact fatigue life of Glare.
| Published in | World Journal of Applied Physics (Volume 5, Issue 2) |
| DOI | 10.11648/j.wjap.20200502.11 |
| Page(s) | 21-33 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2020. Published by Science Publishing Group |
Progressive Damage, Low Velocity Impact, Fatigue Life, Glass-Fiber-Reinforced Aluminum Laminates
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APA Style
Alireza Sedaghat, Majid Alitavoli, Abolfazl Darvizeh, Reza Ansari Khalkhali. (2020). Numerical and Experimental Assessment of Post Impact Fatigue Life of Glass-fiber-reinforced Aluminum Laminates. World Journal of Applied Physics, 5(2), 21-33. https://doi.org/10.11648/j.wjap.20200502.11
ACS Style
Alireza Sedaghat; Majid Alitavoli; Abolfazl Darvizeh; Reza Ansari Khalkhali. Numerical and Experimental Assessment of Post Impact Fatigue Life of Glass-fiber-reinforced Aluminum Laminates. World J. Appl. Phys. 2020, 5(2), 21-33. doi: 10.11648/j.wjap.20200502.11
AMA Style
Alireza Sedaghat, Majid Alitavoli, Abolfazl Darvizeh, Reza Ansari Khalkhali. Numerical and Experimental Assessment of Post Impact Fatigue Life of Glass-fiber-reinforced Aluminum Laminates. World J Appl Phys. 2020;5(2):21-33. doi: 10.11648/j.wjap.20200502.11
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Download@article{10.11648/j.wjap.20200502.11,
author = {Alireza Sedaghat and Majid Alitavoli and Abolfazl Darvizeh and Reza Ansari Khalkhali},
title = {Numerical and Experimental Assessment of Post Impact Fatigue Life of Glass-fiber-reinforced Aluminum Laminates},
journal = {World Journal of Applied Physics},
volume = {5},
number = {2},
pages = {21-33},
doi = {10.11648/j.wjap.20200502.11},
url = {https://doi.org/10.11648/j.wjap.20200502.11},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.wjap.20200502.11},
abstract = {In this research, dynamic progressive failure of Glass-Fiber-Reinforced aluminum laminates under low-energy impact was modelled. Intralaminar damage models, strain-based damage evolution laws, Puck failure criteria were used in ABAQUS-VUMAT software for modelling. Bilinear cohesive model was used for interface delamination, and the Johnson-Cook models were employed for aluminum layers. Damage evolution behaviours of this hybrid composite were calculated. After that, energy dissipation mechanisms were examined to identify the progressive failure and delamination of composite layers and plastic deformation of aluminum layers. In order to determine stress intensity at crack tip, the analytical model for constant-amplitude fatigue crack propagation according to Paris law was applied. Also, bridging stress along crack length in aluminum layer was investigated by correlation between the delamination growth rate and energy release rate in hybrid composite layers. The obtained findings indicated that the highest amount of peak low velocity impact force belonged to Glare 4 3/2. The presented numerical method based on bridging stress phenomena can successfully be used for predicting the post impact fatigue life of Glare.},
year = {2020}
}
TY - JOUR T1 - Numerical and Experimental Assessment of Post Impact Fatigue Life of Glass-fiber-reinforced Aluminum Laminates AU - Alireza Sedaghat AU - Majid Alitavoli AU - Abolfazl Darvizeh AU - Reza Ansari Khalkhali Y1 - 2020/11/04 PY - 2020 N1 - https://doi.org/10.11648/j.wjap.20200502.11 DO - 10.11648/j.wjap.20200502.11 T2 - World Journal of Applied Physics JF - World Journal of Applied Physics JO - World Journal of Applied Physics SP - 21 EP - 33 PB - Science Publishing Group SN - 2637-6008 UR - https://doi.org/10.11648/j.wjap.20200502.11 AB - In this research, dynamic progressive failure of Glass-Fiber-Reinforced aluminum laminates under low-energy impact was modelled. Intralaminar damage models, strain-based damage evolution laws, Puck failure criteria were used in ABAQUS-VUMAT software for modelling. Bilinear cohesive model was used for interface delamination, and the Johnson-Cook models were employed for aluminum layers. Damage evolution behaviours of this hybrid composite were calculated. After that, energy dissipation mechanisms were examined to identify the progressive failure and delamination of composite layers and plastic deformation of aluminum layers. In order to determine stress intensity at crack tip, the analytical model for constant-amplitude fatigue crack propagation according to Paris law was applied. Also, bridging stress along crack length in aluminum layer was investigated by correlation between the delamination growth rate and energy release rate in hybrid composite layers. The obtained findings indicated that the highest amount of peak low velocity impact force belonged to Glare 4 3/2. The presented numerical method based on bridging stress phenomena can successfully be used for predicting the post impact fatigue life of Glare. VL - 5 IS - 2 ER -
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