NUMERICAL MATERIAL MODEL FOR COMPOSITE LAMINATES IN HIGH–VELOCITY IMPACT SIMULATION

Abstract

A NUMERICAL MATERIAL MODEL FOR COMPOSITE LAMINATE, WAS DEVELOPED AND INTEGRATED INTO THE NONLINEAR DYNAMIC EXPLICIT FINITE ELEMENT PROGRAMS AS A MATERIAL USER SUBROUTINE. THIS MODEL COUPLING NONLINEAR STATE OF EQUATION, WAS A MACRO-MECHANICS MODEL, WHICH WAS USED TO SIMULATE THE MAJOR MECHANICAL BEHAVIORS OF COMPOSITE LAMINATE UNDER HIGH–VELOCITY IMPACT CONDITIONS. THE BASIC THEO-RETICAL FRAMEWORK OF THE DEVELOPED MATERIAL MODEL WAS INTRODUCED. AN INVERSE FLYER PLATE SIMULATION WAS CONDUCTED, WHICH DEMON-STRATED THE ADVANTAGE OF THE DEVELOPED MODEL IN CHARACTERIZING THE NONLINEAR SHOCK RESPONSE. THE DEVELOPED MODEL AND ITS IMPLE-MENTATION WERE VALIDATED THROUGH A CLASSIC BALLISTIC IMPACT ISSUE, I.E. PROJECTILE IMPACTING ON KEVLAR29/PHENOLIC LAMINATE. THE FAILURE MODES AND BALLISTIC LIMIT VELOCITY WERE ANALYZED, AND A GOOD AGREEMENT WAS ACHIEVED WHEN COMPARING WITH THE ANALYTICAL AND EXPERIMENTAL RESULTS. THE COMPUTATIONAL CAPACITY OF THIS MODEL, FOR KEVLAR/EPOXY LAMINATES WITH DIFFERENT ARCHITECTURES, I.E. PLAIN–WOVEN AND CROSS–PLIED LAMINATES, WAS FURTHER EVALUATED AND THE RESIDUAL VELOCITY CURVES AND DAMAGE CONE WERE ACCURATELY PREDICTED.