  The response of an aircraft fan blade manufactured by composites under the
action of static and impact load has been studied in this report. The modeling
and analysis of the geometry has been done using CASTEM 2007 version. For the
quasi static analysis, the pressure has been incrementally applied until it
satisfies the failure criteria. The deformed configuration, strain, Von-Mises
stress, and the deflection of the blade have been studied. The response of the
system e.g. deformation time history due to the impact of the projectile has
been studied where the Newmark method for the dynamic problem has been
implemented.
