This work investigates the use of two different vibration-based methods for health monitoring of aircraft wings. A finite element model of a simplified wing is used to model and predict the vibration response of an aircraft wing in an intact condition and in the presence of different types and levels of damage. Two main types of damage are considered - cracks and distributed damage. This study first explores the sensitivity of the lower modal frequencies to different damage levels of the studied types. This approach proved capable to detect highest level damage only, for both damage types. Then the employment of the frequency response functions (FRF) subjected to principal components analysis (PCA) and nearest neighbour approach is discussed. This aproach was used to distinguish between damage and no-damage. In the case of distributed damage, it proved quite promising due to detection of well-damage with more than 90 % success rate, including small damage of 10 %. This is an early model-based study which is intended to establish if the considered procedures can be used as damage detection tools.
An investigation on vibration-based damage detection in an aircraft wing scaled model
Schadensuche am FE-Modell eines Flugzeugflügels aufgrund der Vibration
2005
8 Seiten, 1 Bild, 2 Tabellen, 13 Quellen
Conference paper
English
Airworthiness Evaluation of a Scaled Joined-Wing Aircraft
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