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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.

Numerical Material Model for Composite Laminates in High-Velocity Impact Simulation