A Study on Vibration-Based Damage Detection and Location in an Aircraft Wing Scaled Model

Irina Trendafilova

doi:10.4028/www.scientific.net/AMM.3-4.309

Paper Titles

Interaction Effects of Stress Intensity Factors in Parallel Cracks under Transitional Thermal-Loads
p.279

An Inverse Procedure for Determining the Material Constants of Isotropic Square Plates by Impulse Excitation of Vibration
p.287

Rolling Bearings Monitoring and Damage Detection Methodology
p.293

Experimental Application of the Virtual Fields Method to the Identification of Material Properties Using Vibrating Plates
p.303

A Study on Vibration-Based Damage Detection and Location in an Aircraft Wing Scaled Model
p.309

Experimental Determination of SEA Parameters of Stiffened Cylindrical Shell Structure
p.315

Locating Defects Using Dynamic Strain Analysis and Artificial Neural Networks
p.325

High-Resolution Neutron Diffraction for Nondestructive Analysis of Residual Stresses in Polycrystalline Materials
p.331

Measurement on Rotating Mechanical Component by Thermoelasticity
p.337

HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 3-4A Study on Vibration-Based Damage Detection and...

A Study on Vibration-Based Damage Detection and Location in an Aircraft Wing Scaled Model

Abstract:

This study investigates the possibilities for damage detection and location using the vibration response of an aircraft wing. A simplified finite element model of an aircraft wing is used to model its vibration response. The model is subjected to modal analysis- its natural frequencies are estimated and the mode shapes are determined. Two types of damage are considered - localised and distributed. The wing model is divided into a number of volumes. The goal of the study is to investigate the possibility to use the vibration response of an aircraft wing and especially its modal characteristics for the purposes of damage detection. So we’ll be trying to find suitable features, which can be used to detect damage and restrict it to one of the introduced volumes. The sensitivity of the modal frequencies of the model to damage in different locations is studied. Some general trends in the behaviour of these frequencies with change of the damage location are investigated. The utilization of the modal frequencies for detecting damage in a certain part of the wing is discussed