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Structural Design and Stress Analysis of a Micro Aircraft Wing in a Student Competition


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DOI: https://doi.org/10.15866/irease.v16i6.23878

Abstract


This study focuses on investigating the structural design and stress analysis of a micro aircraft using 3D computer-aided design software. Four distinct wing geometries were designed, each featuring unique wing shapes and dimensions. The maximum stress and deformation tolerances for each wing design were determined through static structural analysis and simulation, identifying potential weak points. The results were analyzed to identify the wing configuration with superior structural performance. The aircraft structure was constructed using balsa wood and polystyrene, while lift factor, air density, velocity, and wing area served as input variables for lift force simulation. A comparative evaluation system based on lift-to-drag ratio, structural strength, stability and control, ease of fabrication, and maneuverability was employed to compare the four designs. The trapezoidal wing design demonstrated the highest design evaluation points, making it the optimal choice among the four. The findings of this study provide valuable insights into stress analysis and structural design of micro airplanes, guiding future investigations and advancements in this domain.
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Keywords


Aircraft Design; Micro Aircraft; Stress Analysis; Wing Design; Student Competition

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References


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