The Impact Behaviour of Carbon Fiber-Epoxy Composite Leading Edge using Finite Element Method
O. Nurihan1, Y. Aminanda2, J.S.M Ali3, Z.A. Rasid4, Y. Hafizal5
1O. Nurihan, MJIIT UTM, Kuala Lumpur, Malaysia.
2Y. Aminanda, Faculty of Engineering, UTB Brunei Darussalam.
3J.S.M Ali, Kuliyyah of Engineering, IIUM, Gombak, Kuala Lumpur.
4Z.A. Rasid, MJIIT UTM, Kuala Lumpur, Malaysia.
5H. Yahaya, MJIIT UTM, Kuala Lumpur, Malaysia.
Manuscript received on 01 March 2019 | Revised Manuscript received on 09 March 2019 | Manuscript published on 30 July 2019 | PP: 2617-2622 | Volume-8 Issue-2, July 2019 | Retrieval Number: B3013078219/19©BEIESP | DOI: 10.35940/ijrte.B3013.078219
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: Composite material has been widely used in aircrafts due to its high strength to weight ratio that leads to weight saving of the aircrafts. Equally important, aircraft material should be tough i.e. it should have the ability to absorb high energy and thus resist fracture. The aircraft’s wing design requires the material to have high toughness as parts of the wing especially its leading edge is subjected to impact loadings. Using finite element software of LS-DYNA, this research focuses on studying the impact behaviour of composite panels that represent the leading edges of wings when the panels are subjected to rigid sphere projectile. Three shapes of panels are used: flat, semi-circular and semi ellipse while panels can be of 2, 4 and 8 layers to vary its thickness. The panels are made of laminated composites with woven carbon fibres and the angle of orientations are [0/90] n, [0/45]n and [45/-45]n where n will give the number of layer for the composite. The Mat-58 material type suitable for woven type fibre is used where failure criteria of Hashin is applied. It was found that the simulation results are in a very close agreement with the finding from experiments conducted earlier. Furthermore, the optimum stacking sequence was found to be the [0/45]2 stacking sequences
Index Terms: Energy Absorption, FEA Simulation, Impact Loading, Leading Edge.
Scope of the Article: Behaviour of Structures