Analisis Kegagalan Laminasi Komposit Epoksi/Serat Karbon Pada Sayap Pesawat Tanpa Awak

Abstract

This study aims to analyze the initial failure value using the Tsai – Wu criteria from the wing skin of an unmanned aircraft with the Eppler 214 airfoil model. The study was carried out using computer modeling with Abaqus software. The material used is an epoxy composite which is carbon fiber. The composites used in the wing skins have two different arrangement sequences, namely the fiber layer arrangement sequence 1 [00/900]8s and the layer sequence 2 [00/+450/-450/900]2s. The load given to the wing is a pressure of 0.40077 MPa. The results for the fiber layer sequence 1 [00/900]8s at the maximum stress distribution are 5.067 x 104 MPa and in the fiber layer sequence, 2 [00/+450/-450/900]2s the maximum value is 4.205 x 104 MPa. While the sequences consist of fiber layer 1 and layer 2 sequence layers, the Tsai – Wu failure meets the Tsai – Wu failure criteria because almost all of them fail

Analysis of Tensile and Bending Strength of Coconut Fiber Reinforcement Composite on Quasi Isotropic Laminates Stacking Sequence

“…The orientation of the fiber direction greatly determines the strength of the composite relative to the existing stress distribution (Adamy et al, 2020) (Roza & Dirhamsyah, 2015), conducted research with the materials used including coconut fiber powder, sengon wood, urea formaldehyde (UF) binder, 25% emulsion (paraffin) 40% and catalyst (NH4CL) (Roza & Dirhamsyah, 2015). Research on epoxy/carbon fiber composite laminates on unmanned aircraft wings was reported by (Siregar & Arief, 2022). The research of effect of stacking sequence on Charpy impact and flexural damage behavior of composite laminates (Caminero et al, 2016).…”