Published in Journal of Industrial Engineering and Robotics, Volume 7, Number 3
Written by CIUDIN Sabina
Scientific coordinators: Prof. dr. ing. Ștefan SOROHAN, Conf. dr. ing. Viorel ANGHEL

This article investigates the buckling behaviour of stiffened panels commonly used in aeronautical engineering. Stiffened panels play a critical role in aircraft structures, providing structural integrity and load-bearing capabilities. The article outlines the analytical approach based on classical plate theory and a finite element method (FEM) analysis of a simply supported thin plate. This example highlights the applicability of both approaches and emphasizes the role of numerical simulations in complex structural analyses. Moving beyond the simple plate example, the article then focuses on the linear buckling analysis of a stiffened panel that resembles a real aircraft structure. The panel's geometry and boundary conditions are defined to simulate the actual operating conditions of the aircraft. Furthermore, a comparative analysis is conducted to evaluate the buckling performance of a similar panel without stiffeners. This comparison highlights the essential role of stiffeners in designing aircraft structres.

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