Design, analysis and weight optimization of a UAV wing

• Κύριος συγγραφέας: Βασιλακοπούλου-Τράπαλη, Ιωάννα
• Άλλοι συγγραφείς: Vasilakopoulou-Trapali, Ioanna
• Γλώσσα: English
• Έκδοση: 2022
• Θέματα: UAV wing; Conceptual design; ANSYS FLUENT; CATIA V5; One-way FSI methods; Optimization algorithms; Πτέρυγα UAV; Παραμετρικός σχεδιασμός; Αλγόριθμοι βελτιστοποίησης

This thesis is a study of the design and optimization of a small wing, which will satisfy specific requirements for the mission of an unmanned aerial vehicle. In the design process, the determination of the initial individual values of the construction weight of the air vehicle was carried out by an iterative procedure and the accurate calculation of the wing loading and power loading, W/S and W/P respectively, parameters of the vehicle were estimated by a geometric method through a summary diagram to satisfy all mission requirements simultaneously. The initial estimates in the wing design were validated and redefined in the detailed design phase. This step formed the basis of aerodynamic analyses using the Finite Element Method (FEM) in ANSYS FLUENT software. The model with the initial approximation of the position and dimensions of the internal and external structures of the wing was designed in CATIA V5. At this point, it was necessary to investigate methods of coupling the aerodynamic analyses and structural results through the interaction of the aerodynamic analysis solutions and their application on the wing surface (one-way Fluid-Structure Interaction FSI analysis) to simulate the loads stressing the vehicle in flight and investigate its structural stability under real conditions rather than simplified non-continuous loading. In the experimental configuration of the wing, its structural response was studied with both aluminum alloys and composite materials. Composite materials were applied to minimize the structure weight, and a reduction of up to 50% was achieved. However further optimization of the structure led to the parameterization process of all wing parts and then the application of optimization algorithms by coupling them with the results of the FEM model. Optimal values for the position and thickness of the internal structures (ribs, spars, skin) were determined and a reduction of the structure weight from the initial wing configuration to the parametric design phase of up to 60% was achieved.