Abdullah, Nur Azam (2023) Aerofracturelastic: a study on the Interaction of crack and aeroelastic instability of aircraft and lifting surfaces. In: 4th ITB International Graduate School Conference (IGSC), 6 July 2023, Institut Teknologi Bandung, Indonesia. (Unpublished)
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Abstract
Aeroelasticity and fracture mechanics are well-known fields that can lead to structural failure. However, there is limited focus on assessing the structural integrity of aircraft wings in aerospace applications when subjected to aerodynamic or aeroelastic loads. Current research in the aircraft industry is primarily centered around developing advanced composite wing structures, which have not been extensively explored. These composite materials offer higher strength, allowing for the design of stronger wings capable of withstanding aerodynamic loads and gust turbulence at high altitudes. However, the presence of cracks or damage on the wing surface can pose a severe risk. This study aims to investigate the structural integrity of composite plates under aerodynamic loads, both undamaged and with cracks. The objective is to develop a novel numerical modeling approach to predict the effects of aerodynamic loads, with a focus on flight maneuver safety margins, including determining flutter speeds. Initially, the flutter speed was calculated using a coupled finite element method (FEM) for structural modeling and the doublet lattice method (DLM) in MSC Nastran for unsteady aerodynamic modeling. The structural and aerodynamic models were connected using spline interpolation. Finally, the safety flight envelope for the composite plate was plotted based on regulations provided by the Federal Aviation Regulations (FAR) 23. To predict crack propagation in damaged composite structures, an extended finite element model (XFEM) was implemented, considering the intercorrelation of aerodynamic loads through a Fourier Series Function (FSF). Gust loads were employed to predict aerodynamic loads, producing the same level of maximum deflection analyzed through aero-static analysis. The results indicate that the fiber orientation of the composite plate significantly influences crack propagation under cruising aerodynamic loads. The same procedures were repeated for a wing box prototype developed under a joint program involving Indonesian Aerospace, the National Institute of Aeronautics and Space of Indonesia, and the Agency for Assessment and Application of Technology of Indonesia. In this investigation, wing fracture was studied under the influence of turbulence, specifically discrete gust loads. FSF was used to combine the wingtip deflection under gust load influence, and XFEM was then applied to model crack propagation. The results indicate that the crack propagated near the lower-front skin, close to the wing root.
| Item Type: | Proceeding Paper (Keynote) |
|---|---|
| Uncontrolled Keywords: | Aeroelastic, structural integrity, doublet lattice method, gust load |
| Subjects: | T Technology > TJ Mechanical engineering and machinery > TJ181 Mechanical movements T Technology > TJ Mechanical engineering and machinery > TJ227 Machine design and drawing T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500 Aeronautics |
| Kulliyyahs/Centres/Divisions/Institutes (Can select more than one option. Press CONTROL button): | UNSPECIFIED |
| Depositing User: | Dr. Nur Azam Abdullah |
| Date Deposited: | 27 Dec 2023 12:14 |
| Last Modified: | 27 Dec 2023 12:14 |
| URI: | http://irep.iium.edu.my/id/eprint/109246 |
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