The experimental study of fastener pull-through failure in composite laminates reported in Part 1 of this paper found pull though faille to be characterized by substantial internal damage similar to that observed for low-velocity impact composite panels. Damage is manifested in form of a conical distributed new tower of matrix cracking and delaminating extending through-the-thickens from the fattener head outer edge, directed away from the fastener hole. Analysis is conducted in this paper to identify the mechanisms responsible for the matrix cracking in this region. Tensile in-plane stresses are the cause of flexural failures found elsewhere in laminates of reduced bending stiffness. Fastener pull-through failure results from the tensile strength of the resin being exceeded.
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