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Finite element analysis of composites materials for aerospace applications

Composites materials are intended to be used more extensively as an alternative of aluminum structure in aircraft and aerospace applications. This is due to their attractive properties as high strength-to-weight ratio and stiffness-to-weight ratio. Besides that it clarifies the growing interest for...

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Main Authors: Mohamad, Nurhaniza, Mohd Atan, Kamel Ariffin, Ali, Aidy, Mustapha, Faizal, Abdul Wahab, Noraini
Format: Article
Language:English
English
Published: 2010
Online Access:http://psasir.upm.edu.my/id/eprint/11950/1/Finite%20element%20analysis%20of%20composites%20materials%20for%20aerospace%20applications.pdf
http://psasir.upm.edu.my/id/eprint/11950/
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spelling my.upm.eprints.119502015-10-21T02:55:43Z http://psasir.upm.edu.my/id/eprint/11950/ Finite element analysis of composites materials for aerospace applications Mohamad, Nurhaniza Mohd Atan, Kamel Ariffin Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini Composites materials are intended to be used more extensively as an alternative of aluminum structure in aircraft and aerospace applications. This is due to their attractive properties as high strength-to-weight ratio and stiffness-to-weight ratio. Besides that it clarifies the growing interest for composites materials due to advantages of lightweight, high strength, high stiffness, superior fatigue life, tremendous corrosion resistance and low cost manufacturing. In this study, a finite element analysis (FEA) of fiberglass unidirectional E-type was analyzed in the framework of ABAQUS finite element commercial software. The analysis was done to quantify the mechanical properties and response of unidirectional E-glass in term of tensile, compression and thermal responses. From the analysis, the maximum and minimum values of stress and strain for E-glass 21xK43 Gevetex and Silenka E-glass 1200tex were obtained and stress-strain curve is presented. The ultimate load of failure, elastic behavior, tensile strength and other properties for each laminated plates under tensile and thermal-stress are determined from stress-strain curves. The simulation will run twice for each material where the first simulation based on orientation angles of 45° for ply-1, -45° for ply-2 and 90° for ply-3 while the second simulation, the orientation angles is 0° for all plies. The simulation is successfully conducted and verified by experimental data. 2010 Article PeerReviewed application/pdf en http://psasir.upm.edu.my/id/eprint/11950/1/Finite%20element%20analysis%20of%20composites%20materials%20for%20aerospace%20applications.pdf Mohamad, Nurhaniza and Mohd Atan, Kamel Ariffin and Ali, Aidy and Mustapha, Faizal and Abdul Wahab, Noraini (2010) Finite element analysis of composites materials for aerospace applications. IOP Conference Series: Materials Science and Engineering, 11 (1). ISSN 1757-899X 10.1088/1757-899X/11/1/012010 English
institution Universiti Putra Malaysia
building UPM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Putra Malaysia
content_source UPM Institutional Repository
url_provider http://psasir.upm.edu.my/
language English
English
description Composites materials are intended to be used more extensively as an alternative of aluminum structure in aircraft and aerospace applications. This is due to their attractive properties as high strength-to-weight ratio and stiffness-to-weight ratio. Besides that it clarifies the growing interest for composites materials due to advantages of lightweight, high strength, high stiffness, superior fatigue life, tremendous corrosion resistance and low cost manufacturing. In this study, a finite element analysis (FEA) of fiberglass unidirectional E-type was analyzed in the framework of ABAQUS finite element commercial software. The analysis was done to quantify the mechanical properties and response of unidirectional E-glass in term of tensile, compression and thermal responses. From the analysis, the maximum and minimum values of stress and strain for E-glass 21xK43 Gevetex and Silenka E-glass 1200tex were obtained and stress-strain curve is presented. The ultimate load of failure, elastic behavior, tensile strength and other properties for each laminated plates under tensile and thermal-stress are determined from stress-strain curves. The simulation will run twice for each material where the first simulation based on orientation angles of 45° for ply-1, -45° for ply-2 and 90° for ply-3 while the second simulation, the orientation angles is 0° for all plies. The simulation is successfully conducted and verified by experimental data.
format Article
author Mohamad, Nurhaniza
Mohd Atan, Kamel Ariffin
Ali, Aidy
Mustapha, Faizal
Abdul Wahab, Noraini
spellingShingle Mohamad, Nurhaniza
Mohd Atan, Kamel Ariffin
Ali, Aidy
Mustapha, Faizal
Abdul Wahab, Noraini
Finite element analysis of composites materials for aerospace applications
author_facet Mohamad, Nurhaniza
Mohd Atan, Kamel Ariffin
Ali, Aidy
Mustapha, Faizal
Abdul Wahab, Noraini
author_sort Mohamad, Nurhaniza
title Finite element analysis of composites materials for aerospace applications
title_short Finite element analysis of composites materials for aerospace applications
title_full Finite element analysis of composites materials for aerospace applications
title_fullStr Finite element analysis of composites materials for aerospace applications
title_full_unstemmed Finite element analysis of composites materials for aerospace applications
title_sort finite element analysis of composites materials for aerospace applications
publishDate 2010
url http://psasir.upm.edu.my/id/eprint/11950/1/Finite%20element%20analysis%20of%20composites%20materials%20for%20aerospace%20applications.pdf
http://psasir.upm.edu.my/id/eprint/11950/
_version_ 1643824903380533248
score 13.211869

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