An explicit multiscale model for progressive failure of a complex composite structures

In this paper an explicit multiscale model for composite materials is introduced and expanded upon previous work. Impact damage, which is a nonlinear event, is difficult to model in an implicit solver. Prediction of progressive failure in a composite can be performed with ply level mechanisms and/or micro level mechanisms. Generalized Method of Cells within NASA's Micromechanics Analysis Code was used in this study. It is implemented by the code FEAMAC within the commercial code ABAQUS. Mechanical properties of Epon E 863 were obtained experimentally, and the Bodner-Partom viscoplastic model was adopted for the simulation. The numerical results of various impact speeds of composite airfoil indicated good correlation with the experimental results of the damaged regions.