Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle
A finite element model is developed to determine deformation and stresses on a composite wing of unmanned aerial vehicle (UAV) with a tubercle design at the leading edge of the wing. Tubercles, commonly known as protuberances found on the leading edge of a whale pectoral flipper, offering great perf...
| Main Authors: | , , , , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Elsevier
2019
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| Online Access: | http://psasir.upm.edu.my/id/eprint/81007/ http://psasir.upm.edu.my/id/eprint/81007/1/FINITE.pdf |
| _version_ | 1848859000895963136 |
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| author | Basri, Ernnie Illyani Mustapha, Faizal Hameed Sultan, Mohamed Thariq Basri, Adi Azriff Abas, Mohd Firdaus Abdul Majid, Mohd Shukry Ahmad, Kamarul Arifin |
| author_facet | Basri, Ernnie Illyani Mustapha, Faizal Hameed Sultan, Mohamed Thariq Basri, Adi Azriff Abas, Mohd Firdaus Abdul Majid, Mohd Shukry Ahmad, Kamarul Arifin |
| author_sort | Basri, Ernnie Illyani |
| building | UPM Institutional Repository |
| collection | Online Access |
| description | A finite element model is developed to determine deformation and stresses on a composite wing of unmanned aerial vehicle (UAV) with a tubercle design at the leading edge of the wing. Tubercles, commonly known as protuberances found on the leading edge of a whale pectoral flipper, offering great performance from an aerodynamic perspective. This paper deals with a first order shear deformation theory (FSDT) approach to discover the UAV laminates composite wing model of tubercle leading edge (TLE) with rib-reinforced so that the equivalent stiffness and material properties are obtained from the simulation of finite element analysis using ANSYS. Another structural configuration of design replicating the idea of monocoque concept, whereby foam is used at the leading and trailing edges of the wing. Styrene acrylonitrile (SAN) core foam is used representing high strength-to-weight ratio with its superiority in the mechanical properties of polymeric sandwich composites. The updated static structural analysis from rib-reinforced can be applied to update the wing stiffness distribution of monocoque-foam. The optimum design is concluded from the tabulated deformation and stresses of both wings, where monocoque-foam showed better performance with a reduction in 50.72% of deformation and 35.88% of stress, compared to rib-reinforced design. |
| first_indexed | 2025-11-15T12:22:23Z |
| format | Article |
| id | upm-81007 |
| institution | Universiti Putra Malaysia |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-15T12:22:23Z |
| publishDate | 2019 |
| publisher | Elsevier |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | upm-810072020-10-14T19:22:31Z http://psasir.upm.edu.my/id/eprint/81007/ Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle Basri, Ernnie Illyani Mustapha, Faizal Hameed Sultan, Mohamed Thariq Basri, Adi Azriff Abas, Mohd Firdaus Abdul Majid, Mohd Shukry Ahmad, Kamarul Arifin A finite element model is developed to determine deformation and stresses on a composite wing of unmanned aerial vehicle (UAV) with a tubercle design at the leading edge of the wing. Tubercles, commonly known as protuberances found on the leading edge of a whale pectoral flipper, offering great performance from an aerodynamic perspective. This paper deals with a first order shear deformation theory (FSDT) approach to discover the UAV laminates composite wing model of tubercle leading edge (TLE) with rib-reinforced so that the equivalent stiffness and material properties are obtained from the simulation of finite element analysis using ANSYS. Another structural configuration of design replicating the idea of monocoque concept, whereby foam is used at the leading and trailing edges of the wing. Styrene acrylonitrile (SAN) core foam is used representing high strength-to-weight ratio with its superiority in the mechanical properties of polymeric sandwich composites. The updated static structural analysis from rib-reinforced can be applied to update the wing stiffness distribution of monocoque-foam. The optimum design is concluded from the tabulated deformation and stresses of both wings, where monocoque-foam showed better performance with a reduction in 50.72% of deformation and 35.88% of stress, compared to rib-reinforced design. Elsevier 2019 Article PeerReviewed text en http://psasir.upm.edu.my/id/eprint/81007/1/FINITE.pdf Basri, Ernnie Illyani and Mustapha, Faizal and Hameed Sultan, Mohamed Thariq and Basri, Adi Azriff and Abas, Mohd Firdaus and Abdul Majid, Mohd Shukry and Ahmad, Kamarul Arifin (2019) Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle. Journal of Materials Research and Technology-JMR&T, 8 (5). pp. 4374-4386. ISSN 2238-7854 https://www.sciencedirect.com/science/article/pii/S2238785419301413 10.1016/j.jmrt.2019.07.049 |
| spellingShingle | Basri, Ernnie Illyani Mustapha, Faizal Hameed Sultan, Mohamed Thariq Basri, Adi Azriff Abas, Mohd Firdaus Abdul Majid, Mohd Shukry Ahmad, Kamarul Arifin Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle |
| title | Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle |
| title_full | Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle |
| title_fullStr | Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle |
| title_full_unstemmed | Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle |
| title_short | Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle |
| title_sort | conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle |
| url | http://psasir.upm.edu.my/id/eprint/81007/ http://psasir.upm.edu.my/id/eprint/81007/ http://psasir.upm.edu.my/id/eprint/81007/ http://psasir.upm.edu.my/id/eprint/81007/1/FINITE.pdf |