Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading
In this study, a dynamic impact loading using Finite Element Analyses (FEA) was applied to an Unmanned Aerial Vehicle (UAV) composite skin panel. Two types of boundary condition panels were investigated (Fixed and Pinned). The composite UAV skin panel consists of upper panel and stiffener which have...
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| Format: | Article |
| Language: | English |
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Teknik mesin, Fakultas Teknik, Universitas Sebelas Maret
2024-03-01
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| Series: | Mekanika |
| Online Access: | https://jurnal.uns.ac.id/mekanika/article/view/77875 |
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| author | Ilham Bagus Wiranto Sherly Octavia Saraswati Iqbal Reza Alfikri Chairunnisa Chairunnisa Fadli Cahya Megawanto Muhammad Ilham Adhynugraha Nur Cholis Majid |
| author_facet | Ilham Bagus Wiranto Sherly Octavia Saraswati Iqbal Reza Alfikri Chairunnisa Chairunnisa Fadli Cahya Megawanto Muhammad Ilham Adhynugraha Nur Cholis Majid |
| author_sort | Ilham Bagus Wiranto |
| collection | DOAJ |
| description | In this study, a dynamic impact loading using Finite Element Analyses (FEA) was applied to an Unmanned Aerial Vehicle (UAV) composite skin panel. Two types of boundary condition panels were investigated (Fixed and Pinned). The composite UAV skin panel consists of upper panel and stiffener which have a thickness of 3 mm and 2 mm, respectively. The material properties used in this study was referring to Hexcel W3G282-F593 technical data sheet. A hemispherical steel indenter with 70 mm diameter and 120 kg of mass was used to crush the panel with a velocity of 4.43 m/s. The finite element analyses were performed using dynamic explicit solver in ABAQUS 6.23. At the beginning of study, the mesh convergence study was conducted to choose the proper mesh for main analysis. The convergence study was simulated using 20 kg mass to shorten computational time. The mesh size of 10 mm was chosen for the main analysis due to convergent result and short computational time compared to others mesh size. The impact deformation, contact force-displacement plot, and contact force-time plot was used to show the differences of using those boundary condition. The results show that fixed and pinned boundary condition reaches its contact force peak with the value of 29.2 kN and 22.8 kN, respectively. |
| format | Article |
| id | doaj-art-71be2a4e5e514201a6e30730ef9627fd |
| institution | Kabale University |
| issn | 1412-7962 2579-3144 |
| language | English |
| publishDate | 2024-03-01 |
| publisher | Teknik mesin, Fakultas Teknik, Universitas Sebelas Maret |
| record_format | Article |
| series | Mekanika |
| spelling | doaj-art-71be2a4e5e514201a6e30730ef9627fd2025-08-20T03:53:38ZengTeknik mesin, Fakultas Teknik, Universitas Sebelas MaretMekanika1412-79622579-31442024-03-01231223210.20961/mekanika.v23i1.7787541620Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact LoadingIlham Bagus Wiranto0Sherly Octavia Saraswati1Iqbal Reza Alfikri2Chairunnisa Chairunnisa3Fadli Cahya Megawanto4Muhammad Ilham Adhynugraha5Nur Cholis Majid6Research Center for Process and Manufacturing Industry Technology, Badan Riset dan Inovasi NasionalResearch Center for Process and Manufacturing Industry Technology, Badan Riset dan Inovasi NasionalResearch Center for Process and Manufacturing Industry Technology, Badan Riset dan Inovasi NasionalResearch Center for Energy Conversion and Conservation, Badan Riset dan Inovasi NasionalResearch Center for Aeronautics Technology, Badan Riset dan Inovasi NasionalResearch Center for Aeronautics Technology, Badan Riset dan Inovasi NasionalMechanical Engineering Department, King Abdulaziz University, Jeddah, Kingdom of Saudi ArabiaIn this study, a dynamic impact loading using Finite Element Analyses (FEA) was applied to an Unmanned Aerial Vehicle (UAV) composite skin panel. Two types of boundary condition panels were investigated (Fixed and Pinned). The composite UAV skin panel consists of upper panel and stiffener which have a thickness of 3 mm and 2 mm, respectively. The material properties used in this study was referring to Hexcel W3G282-F593 technical data sheet. A hemispherical steel indenter with 70 mm diameter and 120 kg of mass was used to crush the panel with a velocity of 4.43 m/s. The finite element analyses were performed using dynamic explicit solver in ABAQUS 6.23. At the beginning of study, the mesh convergence study was conducted to choose the proper mesh for main analysis. The convergence study was simulated using 20 kg mass to shorten computational time. The mesh size of 10 mm was chosen for the main analysis due to convergent result and short computational time compared to others mesh size. The impact deformation, contact force-displacement plot, and contact force-time plot was used to show the differences of using those boundary condition. The results show that fixed and pinned boundary condition reaches its contact force peak with the value of 29.2 kN and 22.8 kN, respectively.https://jurnal.uns.ac.id/mekanika/article/view/77875 |
| spellingShingle | Ilham Bagus Wiranto Sherly Octavia Saraswati Iqbal Reza Alfikri Chairunnisa Chairunnisa Fadli Cahya Megawanto Muhammad Ilham Adhynugraha Nur Cholis Majid Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading Mekanika |
| title | Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading |
| title_full | Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading |
| title_fullStr | Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading |
| title_full_unstemmed | Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading |
| title_short | Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading |
| title_sort | effect of boundary condition on numerical study of uav composite skin panels under dynamic impact loading |
| url | https://jurnal.uns.ac.id/mekanika/article/view/77875 |
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