The analysis models of carbon fiber reinforced epoxy laminates with cylindrical and step shape preembedded
metal part are built based on the application of embedded metal part in composite laminates. The single
layer in the laminates is assumed as three dimensional orthotropic material. The stress analysis of the laminates with
embedded metal part is carried out by finite element method. The distributions of material principal direction stress of
the single layers and the von mises stress of metal part are given. The ultimate loads of the composite laminates are
determined based on the strength criterion of maximum stress. It is shown that the initial damages of the two models
both occur in the 90°layer, and the damage mode is matrix cracking under tension. The initial damage of the laminates
with cylindrical embedded metal part occurs at the twelve o’clock location of the central hole border, and the
initial damage of the laminates with step shape embedded metal part occurs at the six o’clock location of the border
between the No. 7th layer and the pre-embedded metal part. Owing to the more discontinuous carbon fibers, the ultimate
load of the laminates with step shape metal part is smaller than that of the laminates with cylindrical metal part
by 18． 03%.