Localizing Delamination Damages in Aircraft Panels from Modal Damping Parameters

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