Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading

Ilham Bagus Wiranto, Sherly Octavia Saraswati, Iqbal Reza Alfikri, Chairunnisa Chairunnisa, Fadli Cahya Megawanto, Muhammad Ilham Adhynugraha, Nur Cholis Majid

Abstract

In this study, a dynamic impact loading using finite element analyses (FEA) was applied to a 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. 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. The impact deformation, contact force - displacement plot, and contact force – time plot was used to show the differences of using those boundary condition

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DOI: https://doi.org/10.20961/mekanika.v23i1.77875

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