Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method

This paper presents an investigation on flutter speed of cracked composite plates. This work is divided into two sections: (a) variation of crack length at a fixed location on the plate, and (b) variation of crack location on the plate with a fixed crack length, modelled as a unidirectional compos...

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Main Authors:	Abdullah, Nur Azam, Curiel-Sosa, Jose Luis, Akbar, Mahesa
Format:	Article
Language:	English English
Published:	Elsevier 2018
Subjects:	QC Physics T Technology (General) T175 Industrial research. Research and development TJ1425 Lifting and pressing machinery TJ170 Mechanics applied to machinery. Dynamics
Online Access:	http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/7/73583%20Aeroelastic%20assessment%20of%20cracked%20composite.pdf http://irep.iium.edu.my/73583/8/73583%20Aeroelastic%20assessment%20of%20cracked%20composite%20SCOPUS.pdf

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spelling	iium-735832019-08-19T03:14:00Z http://irep.iium.edu.my/73583/ Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method Abdullah, Nur Azam Curiel-Sosa, Jose Luis Akbar, Mahesa QC Physics T Technology (General) T175 Industrial research. Research and development TJ1425 Lifting and pressing machinery TJ170 Mechanics applied to machinery. Dynamics This paper presents an investigation on flutter speed of cracked composite plates. This work is divided into two sections: (a) variation of crack length at a fixed location on the plate, and (b) variation of crack location on the plate with a fixed crack length, modelled as a unidirectional composite for 00,900 and 1350 orientations. Mori- Tanaka homogenization model is applied to obtain the effective composite constitutive properties as the function of fiber and matrix volume fraction. Doublet Lattice Method (DLM) is used to calculate the unsteady aerodynamic forces, i.e., lift distributions. It is found that the existence of small crack ratio on the composite plate (less than 0.4) has triggered an increment of the flutter speed. To support this statement, flutter response modes for each crack ratio are plotted, where the structure appears to be more stiffened than the undamaged plate. However, the crack results in the reduction of flutter speed when the crack ratio reaches 0.5. For the crack location assessment, the flutter speed increases as the crack location moves from the root to the tip due to the reduction of flutter frequency. The results show a good agreement with the validation using Strip Theory considering unsteady aerodynamics. Elsevier 2018-10-15 Article PeerReviewed application/pdf en http://irep.iium.edu.my/73583/7/73583%20Aeroelastic%20assessment%20of%20cracked%20composite.pdf application/pdf en http://irep.iium.edu.my/73583/8/73583%20Aeroelastic%20assessment%20of%20cracked%20composite%20SCOPUS.pdf Abdullah, Nur Azam and Curiel-Sosa, Jose Luis and Akbar, Mahesa (2018) Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method. Composite Structures, 202 (SI:Ian Marshall). pp. 151-161. ISSN 0263-8223 https://www.sciencedirect.com/science/article/pii/S026382231733266X 10.1016/j.compstruct.2018.01.015
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	QC Physics T Technology (General) T175 Industrial research. Research and development TJ1425 Lifting and pressing machinery TJ170 Mechanics applied to machinery. Dynamics
spellingShingle	QC Physics T Technology (General) T175 Industrial research. Research and development TJ1425 Lifting and pressing machinery TJ170 Mechanics applied to machinery. Dynamics Abdullah, Nur Azam Curiel-Sosa, Jose Luis Akbar, Mahesa Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method
description	This paper presents an investigation on flutter speed of cracked composite plates. This work is divided into two sections: (a) variation of crack length at a fixed location on the plate, and (b) variation of crack location on the plate with a fixed crack length, modelled as a unidirectional composite for 00,900 and 1350 orientations. Mori- Tanaka homogenization model is applied to obtain the effective composite constitutive properties as the function of fiber and matrix volume fraction. Doublet Lattice Method (DLM) is used to calculate the unsteady aerodynamic forces, i.e., lift distributions. It is found that the existence of small crack ratio on the composite plate (less than 0.4) has triggered an increment of the flutter speed. To support this statement, flutter response modes for each crack ratio are plotted, where the structure appears to be more stiffened than the undamaged plate. However, the crack results in the reduction of flutter speed when the crack ratio reaches 0.5. For the crack location assessment, the flutter speed increases as the crack location moves from the root to the tip due to the reduction of flutter frequency. The results show a good agreement with the validation using Strip Theory considering unsteady aerodynamics.
format	Article
author	Abdullah, Nur Azam Curiel-Sosa, Jose Luis Akbar, Mahesa
author_facet	Abdullah, Nur Azam Curiel-Sosa, Jose Luis Akbar, Mahesa
author_sort	Abdullah, Nur Azam
title	Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method
title_short	Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method
title_full	Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method
title_fullStr	Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method
title_full_unstemmed	Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method
title_sort	aeroelastic assessment of cracked composite plate by means of fully coupled finite element and doublet lattice method
publisher	Elsevier
publishDate	2018
url	http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/ http://irep.iium.edu.my/73583/7/73583%20Aeroelastic%20assessment%20of%20cracked%20composite.pdf http://irep.iium.edu.my/73583/8/73583%20Aeroelastic%20assessment%20of%20cracked%20composite%20SCOPUS.pdf
first_indexed	2023-09-18T21:44:19Z
last_indexed	2023-09-18T21:44:19Z
_version_	1777413347923197952

Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method

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