Experimental Modal Analysis Of Large Fuselage Panel For Composite Structure: Contact And Non-Contact Measurement

This paper presents the results of a research activity aimed at assessing the impact of several excitation and measure techniques used on the composite structure on the modal model parameters variability. To this aim, an intensive test campaign is carried out on an aircraft fuselage panel made of composite material. Contact and non-contact 1D and contact 3D measurements were performed. Modal models are extracted from dynamic test data collected during a test campaign on a composite material fuselage panel. Assessment of the excitation method and the measurement technique and directions on the modal model parameters is being made.