The paper present results obtained using Abaqus/Explicit software for predicting the impact damage and failure response of various aircraft structures under high velocity impact loadings. Two types of problems are considered. The first concern the crash simulation of a generic airplane fuselage section and the second concern study of bird strike on typical wing leading edge using both metallic and composite structure. In the case of an aircraft fuselage hitting the ground, both vertical crash test and steep glide slope crash conditions are considered. The main objective was then to develop a methodology for performing such fast transient dynamic simulation tests and to determine in each case the residual velocity as well the various deformation modes associated with particular loading and crash conditions.
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