Integrated approach of computational modal analysis and experimental modal analysis to thorough examination of the dynamic characteristics of aircraft structures

Abstract

This study investigates aircraft structural integrity using Experimental Modal Analysis (EMA) and integrates it with computational methods. The methodology combines advanced tools, including CatiaV5 for design, Hyper-Mesh for meshing, Nastran for computational analysis, and Sim Center 3D for precise accelerometer placement. This integrated approach thoroughly examines the dynamic characteristics of aircraft structures, focusing on natural frequencies, mode shapes, and damping ratios. Computational modal analysis of components like wings, fuselage, and vertical tails revealed critical modal parameters, which were validated through experimental modal analysis using impact hammers and accelerometers. The experimental results closely aligned with computational predictions, highlighting the accuracy of the approach. This study is an advancement in the aircraft structural analysis, reinforcing the reliability of modal analysis in aerospace engineering and offering a robust methodology for designing safer and more efficient aircraft.