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Structural analysis on light aircraft wing /Lim Cee Seek

Structural analysis on light aircraft wing_Lim Cee Seek_A2_2011_NI

Abstract Kaedah Unsur Terhingga (Finite Element Method) merupakan satu teknik yang digunakan untuk menganalisis keadaan sesuatu struktur di bawah beban yang berbeza. Kaedah Unsur Terhingga in menggunakan sistem titik yang dikenali sebagai node untuk membentuk grik yang dikenali sebagai mesh. Titik-titik ini ditetapkan ke dalam struktur pada suatu kepadatan mengikut tahap stres yang dikenakan di tempat tersebut. Manakala, grik-grik ini akan diprogram dengan bahan dan sifat struktur yang akan menentukan bagaimana struktur akan bertindak apabila beban dikenakan. Dalam projek ini, Kaedah Unsur Terhingga digunakan untuk menganalisis sayap dengan menggunakan MSC Patran dan MSC Nastran. Analisis ini mengandungi dua bahagian iaitu struktur dan aerodinamik. Beban aerodinamik ditentukan terlebih dahulu. Dengan beban aerodinamik ini, sayap dimodel dengan menggunakan MSC Patran dan kemudian dianalisis dengan MSC Nastran. Akhirnya, pengiraan secara manual dilakukan untuk menyemak keputusan yang diperolehi daripada MSC Nastran. ______________________________________________________________________________________ Finite Element Method (FEM) is a well established technique for analyzing the behavior of structures subjected to a variety of loads. FEM uses a complex system of points called nodes which make a grid called a mesh. The nodes are assigned at a certain density throughout the material depending on the anticipated stress levels of a particular area. While, the mesh is programmed to contain the material and structural properties which define how the structure will react to certain loading. This project is to perform a Finite Element Analysis on a wing model using MSC Patran and MSC Nastran. The analysis process couples the disciplines of structures and aerodynamics. The aerodynamics load that acted on the wing was firstly determined. With this aerodynamics loading, the wing was modeled using MSC Patran and then analyzed with MSC Natran. Finally, the hand calculation was carried out to verify the result obtained by the MSC Natran. From the analysis, the modification succeeds to reduce 4.34 kg from the original design without causing failure during the level flight condition.

Contributor(s): Lim Cee Seek - Author Primary Item Type: Final Year Project Language: English Subject Keywords: nodes ; aerodynamics ; wing First presented to the public: 5/1/2011 Original Publication Date: 7/31/2019 Previously Published By: Universiti Sains Malaysia Place Of Publication: School of Aerospace Engineering Citation: Extents: Number of Pages - 83 License Grantor / Date Granted:   / ( View License ) Date Deposited 2019-07-31 17:10:05.078 Submitter: Nor Hayati Ismail

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