Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing
The demand of Unmanned Aerial Vehicle (UAV) technology received growing interest from today’s engineers in designing and manufacturing the products within a short time and at reasonable price. The wide availability of modern and developing composite materials and the aid of computer s...
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my-upm-ir.856002021-12-09T04:50:13Z Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing 2020-01 Basri, Ernnie Illyani The demand of Unmanned Aerial Vehicle (UAV) technology received growing interest from today’s engineers in designing and manufacturing the products within a short time and at reasonable price. The wide availability of modern and developing composite materials and the aid of computer systems had made the demand becoming possible and achievable. The proposed research consist of fundamental numerical work and experimental work. The study applied the Finite Element (FE) analysis and developed a standardized numerical approach for structural optimization subjected to tubercles design at the leading edge of NACA4415 wing with composite material, known as FE-ACP simulation. The study is crucial in order to optimize the structural behavior of spherical tubercles pattern at the leading edge of straight, untapered and unswept wing. The previous studies proved its superior aerodynamic advantages from computational fluid dynamics (CFD) perspective on the same tubercles design. Therefore, structural characteristic including the external and internal components of the wing should be taken into consideration to achieve the superiority of high strength-to-weight ratio in regards to the application of UAV. Up-to-date, the simulation software, ANSYS is widely used in solving the FE problems subjected to composite materials. The composite modelling of the wing design is developed using ANSYS Composite PrePost (ACP) module, whereby a preliminary simulation is prepared in terms of the designation of composite materials and its impact of wing deformation. In details, the parametric study is carried out, by which the structure of the wing is optimized through optimal composite ply orientation and optimal design configuration subjected to wing stiffness and also criticality of loading requirements for structural failure. Failure criteria of Tsai-Wu and Hashin play important role in determining the optimal design of tubercles wing subjected to strength and stiffness, which is able to be obtained. The experimental study of the designation of composite at the wing skin is conducted in order to prove the simulation validity through material characteristics. Hence, from this study, 50.27% improvement is obtained by applying the TLE wing design with semi-monocoque-foam-reinforced proven the significant of current research area on optimal performance of wing in the perspectives of composite structural optimization. Aeronautical engineering Drone aircraft 2020-01 Thesis http://psasir.upm.edu.my/id/eprint/85600/ http://psasir.upm.edu.my/id/eprint/85600/1/FK%202020%2056%20-%20ir.pdf text en public doctoral Universiti Putra Malaysia Aeronautical engineering Drone aircraft Ahmad, Kamarul Arifin |
| institution |
Universiti Putra Malaysia |
| collection |
PSAS Institutional Repository |
| language |
English |
| advisor |
Ahmad, Kamarul Arifin |
| topic |
Aeronautical engineering Drone aircraft |
| spellingShingle |
Aeronautical engineering Drone aircraft Basri, Ernnie Illyani Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing |
| description |
The demand of Unmanned Aerial Vehicle (UAV) technology received growing interest from today’s
engineers in designing and manufacturing the products within a short time and at reasonable
price. The wide availability of modern and developing composite materials and the aid of computer
systems had made the demand becoming possible and achievable. The proposed research consist of
fundamental numerical work and experimental work. The study applied the Finite Element (FE)
analysis and developed a standardized numerical approach for structural optimization subjected
to tubercles design at the leading edge of NACA4415 wing with composite material, known
as FE-ACP simulation. The study is crucial in order to optimize the structural behavior of
spherical tubercles pattern at the leading edge of straight, untapered and unswept wing.
The previous studies proved its superior aerodynamic advantages from
computational fluid dynamics (CFD) perspective on the same tubercles design. Therefore,
structural characteristic including the external and internal components of the wing
should be taken into consideration to achieve the superiority of high strength-to-weight
ratio in regards to the application of UAV. Up-to-date, the simulation software, ANSYS is
widely used in solving the FE problems subjected to composite materials. The composite modelling
of the wing design is developed using ANSYS Composite PrePost (ACP) module, whereby a preliminary
simulation is prepared in terms of the designation of composite materials and its impact of wing
deformation. In details, the parametric study is carried out, by which the structure of the
wing is optimized through optimal composite ply orientation and optimal design
configuration subjected to wing stiffness and also criticality of loading requirements for
structural failure. Failure criteria of Tsai-Wu and Hashin play important role in determining
the optimal design of tubercles wing subjected to strength and stiffness, which is able to be
obtained. The experimental study of the designation of composite at the wing skin is conducted
in order to prove the simulation validity through material characteristics. Hence, from this study, 50.27% improvement is obtained by applying the
TLE wing design with semi-monocoque-foam-reinforced proven the significant of current research
area on optimal performance of wing in the
perspectives of composite structural optimization. |
| format |
Thesis |
| qualification_level |
Doctorate |
| author |
Basri, Ernnie Illyani |
| author_facet |
Basri, Ernnie Illyani |
| author_sort |
Basri, Ernnie Illyani |
| title |
Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing |
| title_short |
Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing |
| title_full |
Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing |
| title_fullStr |
Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing |
| title_full_unstemmed |
Numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing |
| title_sort |
numerical analysis of tubercles leading edge for unmanned aerial vehicle composite wing |
| granting_institution |
Universiti Putra Malaysia |
| publishDate |
2020 |
| url |
http://psasir.upm.edu.my/id/eprint/85600/1/FK%202020%2056%20-%20ir.pdf |
| _version_ |
1747813567145443328 |