Parametric study on cohesive element for composite fuselage model
In this paper, a numerical simulation on a new fabrication miniature composite fuselage structure- a woven composite laminated with an adhesively bonded butt joint under the axial compression loading is presented. A FEA via Abaqus/Explicit was utilized to capture the complete compressive responses t...
| Main Authors: | , , , , |
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| Format: | Article |
| Language: | English |
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Trans Tech Publications
2011
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| Online Access: | http://psasir.upm.edu.my/id/eprint/23081/1/Parametric%20study%20on%20cohesive%20element%20for%20composite%20fuselage%20model.pdf |
| _version_ | 1796970289732517888 |
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| author | Ng, Wei Sim Mustapha, Faizal Varatharajoo, Renuganth Zahari, Rizal Abang Abdul Majid, Dayang Laila |
| author_facet | Ng, Wei Sim Mustapha, Faizal Varatharajoo, Renuganth Zahari, Rizal Abang Abdul Majid, Dayang Laila |
| author_sort | Ng, Wei Sim |
| collection | UPM |
| description | In this paper, a numerical simulation on a new fabrication miniature composite fuselage structure- a woven composite laminated with an adhesively bonded butt joint under the axial compression loading is presented. A FEA via Abaqus/Explicit was utilized to capture the complete compressive responses to predict the crushing behaviour and its mechanical strength from the initial compression loading till its final failure mode. A woven C-glass fiber/epoxy 200 g/m2 composite laminated [908] with the orthotropic elastic material properties is modeled as a continuum composite layup in the proposed numerical model. The adhesively bonded joint progression was modeled using the cohesive element technique. The proposed model was used to observe the crushing load and collapse modes under the axial compression impact. The finite element results showed a good agreement with the experimental results under the actual quasi-static tests. The validation code was extended to further undergo parametric studies in order to visualise the effect of angle orientations and special laminate cases as to attain the optimum design criteria for the proposed composite structure. |
| first_indexed | 2024-03-06T07:55:50Z |
| format | Article |
| id | upm.eprints-23081 |
| institution | Universiti Putra Malaysia |
| language | English |
| last_indexed | 2024-03-06T07:55:50Z |
| publishDate | 2011 |
| publisher | Trans Tech Publications |
| record_format | dspace |
| spelling | upm.eprints-230812015-12-03T07:16:37Z http://psasir.upm.edu.my/id/eprint/23081/ Parametric study on cohesive element for composite fuselage model Ng, Wei Sim Mustapha, Faizal Varatharajoo, Renuganth Zahari, Rizal Abang Abdul Majid, Dayang Laila In this paper, a numerical simulation on a new fabrication miniature composite fuselage structure- a woven composite laminated with an adhesively bonded butt joint under the axial compression loading is presented. A FEA via Abaqus/Explicit was utilized to capture the complete compressive responses to predict the crushing behaviour and its mechanical strength from the initial compression loading till its final failure mode. A woven C-glass fiber/epoxy 200 g/m2 composite laminated [908] with the orthotropic elastic material properties is modeled as a continuum composite layup in the proposed numerical model. The adhesively bonded joint progression was modeled using the cohesive element technique. The proposed model was used to observe the crushing load and collapse modes under the axial compression impact. The finite element results showed a good agreement with the experimental results under the actual quasi-static tests. The validation code was extended to further undergo parametric studies in order to visualise the effect of angle orientations and special laminate cases as to attain the optimum design criteria for the proposed composite structure. Trans Tech Publications 2011 Article PeerReviewed application/pdf en http://psasir.upm.edu.my/id/eprint/23081/1/Parametric%20study%20on%20cohesive%20element%20for%20composite%20fuselage%20model.pdf Ng, Wei Sim and Mustapha, Faizal and Varatharajoo, Renuganth and Zahari, Rizal and Abang Abdul Majid, Dayang Laila (2011) Parametric study on cohesive element for composite fuselage model. Key Engineering Materials, 471-472. pp. 1085-1090. ISSN 1013-9826; ESSN: 1662-9795 http://www.scientific.net/KEM.471-472.1085 10.4028/www.scientific.net/KEM.471-472.1085 |
| spellingShingle | Ng, Wei Sim Mustapha, Faizal Varatharajoo, Renuganth Zahari, Rizal Abang Abdul Majid, Dayang Laila Parametric study on cohesive element for composite fuselage model |
| title | Parametric study on cohesive element for composite fuselage model |
| title_full | Parametric study on cohesive element for composite fuselage model |
| title_fullStr | Parametric study on cohesive element for composite fuselage model |
| title_full_unstemmed | Parametric study on cohesive element for composite fuselage model |
| title_short | Parametric study on cohesive element for composite fuselage model |
| title_sort | parametric study on cohesive element for composite fuselage model |
| url | http://psasir.upm.edu.my/id/eprint/23081/1/Parametric%20study%20on%20cohesive%20element%20for%20composite%20fuselage%20model.pdf |
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