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Design and optimization of an aeronautical composite laminated panel/Nur Hidayah Idris

Design and optimization of an aeronautical composite laminated panel_Nur Hidayah Idris_A2_2009_NI

Abstract Proses pengoptimuman dari segi pengurangan berat bagi satu lapisan lamina bersegi empat tepat dijalankan menggunakan program pengkomputeran MATLAB. Peringkat pertama bagi proses pengoptimuman berhubungan dengan rintangan kegagalan (failure resistance) dan juga memberikan nilai bagi ketebalan minima bagi lamina dan memberikan nilai peratus bagi setiap orientasi gentian fiber. Gentian fiber yang digunakan adalah terhad kepada 0°, 45°, -45°, and 90°. Langkah yang terakhir ialah mendapatkan bilangan lapisan yang paling optimum bagi setiap orientasi ______________________________________________________________________________________ A rectangular composite laminated panel is optimized in terms of mass (weight reduction) using MATLAB programming code. The first level of optimization process deals with failure resistance and defining the minimum thickness of the overall plies and percentage in each fibre orientation. The fibre orientation used are only limited to a sets of (0°, 45°, -45°, and 90°). Rounding process was done after obtaining the minimum thickness of the overall plies and percentage in each fibre orientation. The final results of the entire optimization process program are number of the plies in each fibre orientation.

Contributor(s): Nur Hidayah Idris - Author Primary Item Type: Final Year Project Language: English Subject Keywords: composite laminated ; fibre; thickness First presented to the public: 4/1/2009 Original Publication Date: 5/21/2019 Previously Published By: Universiti Sains Malaysia Place Of Publication: School of Aerospace Engineering Citation: Extents: Number of Pages - 63 License Grantor / Date Granted:   / ( View License ) Date Deposited 2019-05-21 16:34:20.609 Submitter: Nor Hayati Ismail

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