A concept for the identification and localization of delamination damages in CFRP is introduced. The general methodology is lined out and a localization method based on damage-caused modal damping variations is described. Using only scalar damping values requires a correlation of measured data to the corresponding data from a mathematical model in order to gain information on the damage location. A stringer-stiffened aircraft panel is used as a test structure to generate experimental data for an undamaged and damaged case and to assess the proposed concept.
Localizing delamination damages in aircraft panels from modal damping parameters
2001
6 Seiten, 10 Quellen
Conference paper
English
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