Methodology for Selecting a Rational Layout Scheme of a Carbon Fiber Reinforced Plastic Load-Bearing Structure for a Light Aircraft Wing under Aerodynamic Loads
Published: 20.04.2026
Authors: Wai Yan Oo, Mihajlovskiy K.V.
Published in issue: #4(172)/2026
Category: Aviation and Rocket-Space Engineering | Chapter: Strength and Thermal Conditions of Aircraft
The results of optimizing the layout of the load-bearing structure of the wing of the Piper PA-28 light aircraft to ensure the required performance at minimum weight are presented. The optimization problem was carried out in several stages: at the first stage, aerodynamic loads on the wing were determined taking into account six design flight cases; at the second stage, combinations of 45 layout variants of the carbon fiber reinforced plastic load-bearing structure were analyzed to achieve minimum deflection and wing mass, and the optimal variant was identified; at the third stage, safety factors for the elements of the load-bearing structure for this variant under aerodynamic loads were obtained, and quasistatic and structural stability problems were solved. The optimal variants were selected from a set of Pareto-efficient solutions based on the minimum distance to the ideal point. The optimal configuration was identified as the one with a rib spacing of 550 mm and spar locations at 25% and 60% of the wing chord, which makes it possible to reduce the mass by 22.92% and the deflection by 29.06%.
EDN OIGULK
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