Parametric investigations of strength of a composite panel after impact damage

Abstract

Results of parametrical investigations of residual strength and buckling of damaged composite panels of civil aircrafts were considered. The investigations were performed on the base of the semi-empirical method developed by the author. The algorithm allows users to carry out the analysis of parameters of stress-strain state and to assess a general buckling behavior of composite panels in the automatic mode. The calculations were performed by using the special parametrical finite element models of composite panels that are typical for current civil aircrafts. The special models of panels consisted of composite laminated skin and different types of stiffeners have zones with reduced stiffness characteristics. The relationship between level of reducing mechanical characteristics of “damaged” zones and residual strength and buckling margins of the panels was determined.