Finite element analysis of composite materials for aerospace applications
Composite 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 c...
| Main Authors: | , , , , |
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| Format: | Conference or Workshop Item |
| Language: | English |
| Published: |
2009
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| Online Access: | http://psasir.upm.edu.my/id/eprint/50304/1/172-182-NURHANIZA-FINITE_ELEMENT_ANALYSIS_OF_COMPOSITES_MATE.pdf |
| _version_ | 1825930306535817216 |
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| author | Mohamad, Nurhaniza Mohd Ariffin, Mohd Khairol Anuar Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini |
| author_facet | Mohamad, Nurhaniza Mohd Ariffin, Mohd Khairol Anuar Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini |
| author_sort | Mohamad, Nurhaniza |
| collection | UPM |
| description | Composite 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 composite 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. |
| first_indexed | 2024-03-06T09:09:35Z |
| format | Conference or Workshop Item |
| id | upm.eprints-50304 |
| institution | Universiti Putra Malaysia |
| language | English |
| last_indexed | 2024-03-06T09:09:35Z |
| publishDate | 2009 |
| record_format | dspace |
| spelling | upm.eprints-503042017-03-01T09:44:39Z http://psasir.upm.edu.my/id/eprint/50304/ Finite element analysis of composite materials for aerospace applications Mohamad, Nurhaniza Mohd Ariffin, Mohd Khairol Anuar Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini Composite 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 composite 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. 2009 Conference or Workshop Item PeerReviewed application/pdf en http://psasir.upm.edu.my/id/eprint/50304/1/172-182-NURHANIZA-FINITE_ELEMENT_ANALYSIS_OF_COMPOSITES_MATE.pdf Mohamad, Nurhaniza and Mohd Ariffin, Mohd Khairol Anuar and Ali, Aidy and Mustapha, Faizal and Abdul Wahab, Noraini (2009) Finite element analysis of composite materials for aerospace applications. In: 9th National Symposium on Polymeric Materials 2009 (NSPM 2009), 14-16 Dec. 2009, Residence Hotel, Uniten, Putrajaya. (pp. 172-182). |
| spellingShingle | Mohamad, Nurhaniza Mohd Ariffin, Mohd Khairol Anuar Ali, Aidy Mustapha, Faizal Abdul Wahab, Noraini Finite element analysis of composite materials for aerospace applications |
| title | Finite element analysis of composite materials for aerospace applications |
| title_full | Finite element analysis of composite materials for aerospace applications |
| title_fullStr | Finite element analysis of composite materials for aerospace applications |
| title_full_unstemmed | Finite element analysis of composite materials for aerospace applications |
| title_short | Finite element analysis of composite materials for aerospace applications |
| title_sort | finite element analysis of composite materials for aerospace applications |
| url | http://psasir.upm.edu.my/id/eprint/50304/1/172-182-NURHANIZA-FINITE_ELEMENT_ANALYSIS_OF_COMPOSITES_MATE.pdf |
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