PSI - Issue 21

Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2019) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000 – 000 ScienceDirect

www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

ScienceDirect

Procedia Structural Integrity 21 (2019) 206–214

© 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/ Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers Ab tract This study presents the simulation of standard drop-weight imp ct test on a [0/90/0] s composite laminate. For this purpose, a t ree di ensional virtual t st setup i developed in ABAQUS/Explicit finite element tool. Hem spheric l impactor and specimen fixtur are model d as rigid bodies. Composite plate is modeled as a 3-D deformable solid and discretized usi g a biased mesh for computational eff ci ncy. For simulation of ply damage in the composite laminate, a continuum damage mechanics based damage mod l is develop d and i lem nted in o the analysis v a a user-writt n subroutine VUMAT. Dela ination damage is simula ed by inserting co sive lem nts at the i terfaces of pli s having iffere t orientat . Results show that initial failure mechanism in the 3-D low-v locity impact event is the matrix cracking in the low rmost plies indepe d nt from the stacking sequence of the laminate. Furthermore, the simulation accurately predict that delaminated regions expand mainly in the same direction as of the fibers of t lower adjacent layer in accordance with the bending stiffness mismatching concept. © 2019 The Autho s. Publ shed by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/ Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials Simulation of Drop-Weight Impact Test on Composite Laminates using Finite Element Method Mirac Onur Bozkurt a,b , Levend Parnas c , Demirkan Coker a,b, * a Department of Aerospace Engineering, METU, Ankara 06800, Turkey b METU Center for Wind Energy, METU, Ankara 06800, Turkey c Department of Mechanical Engineering, TED University, Ankara 06800, Turkey Abstract This study presents the simulation of standard drop-weight impact test on a [0/90/0] s composite laminate. For this purpose, a three dimensional virtual test setup is developed in ABAQUS/Explicit finite element tool. Hemispherical impactor and specimen fixture are modeled as rigid bodies. Composite plate is modeled as a 3-D deformable solid and discretized using a biased mesh for computational efficiency. For simulation of ply damage in the composite laminate, a continuum damage mechanics based damage model is developed and implemented into the analysis via a user-written subroutine VUMAT. Delamination damage is simulated by inserting cohesive elements at the interfaces of plies having different orientations. Results show that the initial failure mechanism in the 3-D low-velocity impact event is the matrix cracking in the lowermost plies independent from the stacking sequence of the laminate. Furthermore, the simulation accurately predict that delaminated regions expand mainly in the same direction as of the fibers of the lower adjacent layer in accordance with the bending stiffness mismatching concept. 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials Simulation of Drop-Weight Impact Test on C mposite Laminates using Finite Element Method Mirac Onur Bozkurt a,b , Levend Parnas c , Demirkan Coker a,b, * a Department of Aerospace Engineering, METU, Ankara 0680 , Turkey b METU Center for Wind Energy, METU, Ankara 06800, Turkey c Department of Mechanical Engineering, TED University, Ankara 06800, Turkey Keywords: Drop-weight impact; finite element analysis; composite; matrix crack; delamination

Keywords: Drop-weight impact; finite element analysis; composite; matrix crack; delamination

* Corresponding author. Tel.: +90-312-210-4257; fax: +90-312-210-4250. E-mail address: coker@metu.edu.tr

2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/ Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers 2452 3216 © 2019 Th Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/ Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers * Corresponding author. Tel.: +90-312-210-4257; fax: +90-312-210-4250. E mail address: coker@metu.edu.tr

2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers 10.1016/j.prostr.2019.12.103