Parametric investigation on the damage behavior of a CFRP omega reinforced panel subjected to asymmetrical flexural load conditions

This paper investigates the damage behavior of a reinforced composite panel under symmetrical and asymmetrical bending load. The examined reinforced composite structure is a curved CFRP panel and a co-cured CFRP omega stringer. It may be considered a typical stiffened skin section of a regional aircraft fuselage. The bending loading conditions have been simulated by means of three-point bending tests. The aim of the work is a numerical study, performed to study the influence of asymmetric bending loads on intra-laminar and inter-laminar damage, taking into account the different configurations of the panels and the different orientations of the rollers.