Projek tahun akhir ini melibatkan penghasilan model komposit honeycomb sandwich secara tiga dimensi dan pengaplikasiannya sebagai panel luar (‘skin panels’) kepada struktur-struktur lazim kapal terbang. Struktur honeycomb sandwich telah dimodel menggunakan fungsi Composites Design CATIA V5R16 dan kemudiannya dianalisa secara elemen terhingga mengunakan fungsi Generative Structural Analysis CATIA.
Struktur-struktur rangka kapal terbang seperti nose radome, inboard trailing edge mid flap, elevator dan rudder kemudiannya dimodel menggunakan fungsi Part Design dan Wireframe and Surface Design CATIA berdasarkan struktur-struktur sebenar kapal terbang Boeing 747. Struktur-struktur ini kemudiannya dipasang dengan panel luar honeycomb sandwich yang telah dimodel dan kemudiannya dianalisa sebagai satu struktur lengkap menggunakan fungsi Generative Structural Analysis CATIA. Keputusan analisa-analisa tersebut yang merangkumi Von Mises stress, stress principal tensors, deformation dan translational displacement kemudiannya diperhatikan dan diintepretasi. Keputusan akhir menngenai kesesuaian struktur honeycomb sandwich yang dimodel sebagai panel luar struktur-struktur kapal terbang ini dibuat.
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This final year project focuses on the conceptual three-dimensional modelling of a composite honeycomb sandwich structure for use as skin panels to common commercial aircraft airframe structures. The honeycomb sandwich structure was modelled using CATIA V5R16 Composites Design workbench. It is then analysed via finite element analysis using CATIA Generative Structural Analysis workbench. Airframe structures of nose radome, inboard trailing edge mid flap, elevator and rudder was then modelled using CATIA design workbenches, based on the real airframe structures of the Boeing 747, and are assembled with composite skin panels based on the modelled composite honeycomb sandwich structure. The airframe structures are then analysed by finite element analysis using CATIA Generative Structural Analysis workbench and the effects and outcome of Von Misses stress, stress principal tensors, deformation and translational displacements due to static loading on the structures is observed. Conclusion on the suitability of the modelled composite honeycomb sandwich structure as airframe structure skin panels was then made.
Modeling and analysis of aero-composite materials in aircraft structure applications_Mohd Syahiran Mustaffa_A2_2009_NI