Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM

In this paper, a novel procedure to analyse dynamic crack under aeroelastic loading by means of XFEM and Doublet Lattice Method (DLM) - FEM coupling is presented. The present work performed a new investigation on the crack propagation on the composite plate exerted by the unsteady aerodynamic loadi...

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Main Authors:	Abdullah, Nur Azam, Curiel-Sosa, J.L., Wirawan, Nanda, Akbar, Mahesa
Format:	Conference or Workshop Item
Language:	English English
Published:	2018
Subjects:	TL500 Aeronautics TL787 Astronautics
Online Access:	http://irep.iium.edu.my/74973/ http://irep.iium.edu.my/74973/1/7207.pdf http://irep.iium.edu.my/74973/7/74973_Program.pdf

id	iium-74973
recordtype	eprints
spelling	iium-749732019-10-21T02:41:37Z http://irep.iium.edu.my/74973/ Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM Abdullah, Nur Azam Curiel-Sosa, J.L. Wirawan, Nanda Akbar, Mahesa TL500 Aeronautics TL787 Astronautics In this paper, a novel procedure to analyse dynamic crack under aeroelastic loading by means of XFEM and Doublet Lattice Method (DLM) - FEM coupling is presented. The present work performed a new investigation on the crack propagation on the composite plate exerted by the unsteady aerodynamic loading during the cruise speed. The study on whether the failure due to instability, i.e., flutter, comes first or the crack propagates first until the structural failure is focused. The flutter speed is determined, and the maximum cruise speed is assessed based on the regulation guided by the FAR 23. The proposed method is used to solve the limitation in XFEM within Abaqus that only general static and implicit dynamic analysis can be performed. As the propagation of crack should be analyzed, the composite plate is assigned based on the energy release rate (ERR) of that type of material. The influence of a crack growth on a composite plate at cruise speed is shown in some details. Despite the fact that the crack is propagated at this speed, with initial crack ratio of 0.25, the crack has just grown slightly. 2018-07-22 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/74973/1/7207.pdf application/pdf en http://irep.iium.edu.my/74973/7/74973_Program.pdf Abdullah, Nur Azam and Curiel-Sosa, J.L. and Wirawan, Nanda and Akbar, Mahesa (2018) Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM. In: 6th International Conference Integrity-Reliability-Failure, 22-26 Jul 2018, Lisbon, Portugal.
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TL500 Aeronautics TL787 Astronautics
spellingShingle	TL500 Aeronautics TL787 Astronautics Abdullah, Nur Azam Curiel-Sosa, J.L. Wirawan, Nanda Akbar, Mahesa Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM
description	In this paper, a novel procedure to analyse dynamic crack under aeroelastic loading by means of XFEM and Doublet Lattice Method (DLM) - FEM coupling is presented. The present work performed a new investigation on the crack propagation on the composite plate exerted by the unsteady aerodynamic loading during the cruise speed. The study on whether the failure due to instability, i.e., flutter, comes first or the crack propagates first until the structural failure is focused. The flutter speed is determined, and the maximum cruise speed is assessed based on the regulation guided by the FAR 23. The proposed method is used to solve the limitation in XFEM within Abaqus that only general static and implicit dynamic analysis can be performed. As the propagation of crack should be analyzed, the composite plate is assigned based on the energy release rate (ERR) of that type of material. The influence of a crack growth on a composite plate at cruise speed is shown in some details. Despite the fact that the crack is propagated at this speed, with initial crack ratio of 0.25, the crack has just grown slightly.
format	Conference or Workshop Item
author	Abdullah, Nur Azam Curiel-Sosa, J.L. Wirawan, Nanda Akbar, Mahesa
author_facet	Abdullah, Nur Azam Curiel-Sosa, J.L. Wirawan, Nanda Akbar, Mahesa
author_sort	Abdullah, Nur Azam
title	Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM
title_short	Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM
title_full	Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM
title_fullStr	Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM
title_full_unstemmed	Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM
title_sort	structural integrity assessment of cracked composite plate under aeroelastic loading by means of xfem
publishDate	2018
url	http://irep.iium.edu.my/74973/ http://irep.iium.edu.my/74973/1/7207.pdf http://irep.iium.edu.my/74973/7/74973_Program.pdf
first_indexed	2023-09-18T21:46:07Z
last_indexed	2023-09-18T21:46:07Z
_version_	1777413460662943744

Structural integrity assessment of cracked composite plate under aeroelastic loading by means of XFEM

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