PSI - Issue 59

ScienceDirect Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2022) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2022) 000 – 000 Available online at www.sciencedirect.com Procedia Structural Integrity 59 (2024) 230–237

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

© 2024 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of DMDP 2023 Organizers Abstract This study presents the drop mass impact test behavior of a composite stiffened panel using finite element analysis (FEA). The composite panel was a representation of an unmanned aerial vehicle (UAV) fuselage structure, which was simplified and modelled as a stiffened crossbar panel. The panel and stiffener have thicknesses of 2 mm and 3 mm, respectively. Both of those parts were modeled as a woven carbon/epoxy composite. A hemispherical impactor with a diameter of 70 mm was used to study the impact behavior of a composite skin panel. The FEA was performed using a dynamic explicit solver in ABAQUS 6.23. At the beginning of the study, the mesh convergence study was conducted to choose the proper mesh for the main analysis. In addition, the numerical benchmark has also been investigated in this study. The main analysis was performed by varying impact velocities (4.43, 6.26, and 7.67 m/s) and impact mass (50, 100, and 150 kg). Finally, the impact behavior of the composite panel will be discussed thoroughly. © 2024 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of DMDP 2023 Organizers Keywords: Composite stiffened panel, impact loading, Finite Element Analysis Abstract This study presents the drop mass impact test behavior of a composite stiffened panel using finite element analysis (FEA). The composite panel was a representation of an unmanned aerial vehicle (UAV) fuselage structure, which was simplified and modelled as a stiffened crossbar panel. The panel and stiffener have thicknesses of 2 mm and 3 mm, respectively. Both of those parts were modeled as a woven carbon/epoxy composite. A hemispherical impactor with a diameter of 70 mm was used to study the impact behavior of a composite skin panel. The FEA was performed using a dynamic explicit solver in ABAQUS 6.23. At the beginning of the study, the mesh convergence study was conducted to choose the proper mesh for the main analysis. In addition, the numerical benchmark has also been investigated in this study. The main analysis was performed by varying impact velocities (4.43, 6.26, and 7.67 m/s) and impact mass (50, 100, and 150 kg). Finally, the impact behavior of the composite panel will be discussed thoroughly. © 2024 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of DMDP 2023 Organizers Keywords: Composite stiffened panel, impact loading, Finite Element Analysis VII International Conference “In -service Damage of Materials: Diagnostics and Prediction ” (DMDP 2023) Analysis of composite fuselage structure under axial impact loading Ilham Bagus Wiranto a , Sherly Octavia Saraswati a , Aditya Rio Prabowo b,* , Iqbal Reza Al Fikri a , Chairunnisa c , Teguh Muttaqie d , Muhammad Ilham Adhynugraha e , Fadli Cahya Megawanto e , Arif Hidayat f , Abid Paripurna Fuadi g , Aryandi Marta e , Fajar Ari Wandono e , Abian Nurrohmad e VII International Conference “In -service Damage of Materials: Diagnostics and Prediction ” (DMDP 2023) Analysis of composite fuselage structure under axial impact loading Ilham Bagus Wiranto a , Sherly Octavia Saraswati a , Aditya Rio Prabowo b,* , Iqbal Reza Al Fikri a , Chairunnisa c , Teguh Muttaqie d , Muhammad Ilham Adhynugraha e , Fadli Cahya Megawanto e , Arif Hidayat f , Abid Paripurna Fuadi g , Aryandi Marta e , Fajar Ari Wandono e , Abian Nurrohmad e a Research Center for Process and Manufacturing Industry Technology, BRIN, Tangerang 15314, Indonesia b Department of Mechanical Engineering, Universitas Sebelas Maret, Surakarta 57126, Indonesia a Research Center for Process and Manufacturing Industry Technology, BRIN, Tangerang 15314, Indonesia b Department of Mechanical Engineering, Universitas Sebelas Maret, Surakarta 57126, Indonesia c Research Center for Energy Conversion and Conservation, BRIN, Tangerang 15314, Indonesia d Research Center for Testing Technology and Standards, BRIN,Tangerang 15314, Indonesia c Research Center for Energy Conversion and Conservation, BRIN, Tangerang 15314, Indonesia d Research Center for Testing Technology and Standards, BRIN,Tangerang 15314, Indonesia e Research Center for Aeronautics Technology, BRIN, Bogor 16350, Indonesia f Research Center for Advanced Material, BRIN, Tangerang 15314, Indonesia g Research Center for Hydrodynamics Technology, BRIN, Surabaya 60117, Indonesia e Research Center for Aeronautics Technology, BRIN, Bogor 16350, Indonesia f Research Center for Advanced Material, BRIN, Tangerang 15314, Indonesia g Research Center for Hydrodynamics Technology, BRIN, Surabaya 60117, Indonesia

* Corresponding author. Tel.: +62-271-632-163; fax: +62-271-623-163 E-mail address: aditya@ft.uns.ac.id * Corresponding author. Tel.: +62-271-632-163; fax: +62-271-623-163 E-mail address: aditya@ft.uns.ac.id

2452-3216 © 2024 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of DMDP 2023 Organizers 10.1016/j.prostr.2024.04.033 2452-3216 © 2024 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of DMDP 2023 Organizers 2452-3216 © 2024 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of DMDP 2023 Organizers