Analysis of composite fuselage structure under axial impact loading

• Published in: Procedia Structural Integrity 2024, Vol.59, p.230-237
• Main Authors: Wiranto, Ilham Bagus, Saraswati, Sherly Octavia, Prabowo, Aditya Rio, Al Fikri, Iqbal Reza, Chairunnisa, Muttaqie, Teguh, Adhynugraha, Muhammad Ilham, Megawanto, Fadli Cahya, Hidayat, Arif, Fuadi, Abid Paripurna, Marta, Aryandi, Wandono, Fajar Ari, Nurrohmad, Abian
• Format: Article
• Language: English
• Subjects: Composite stiffened panel; Finite Element Analysis; impact loading
• ISSN: 2452-3216; 2452-3216
• DOI: 10.1016/j.prostr.2024.04.033

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.