This thesis work deals with the design of
a guidance control architecture using sliding mode control
for a missile equipped with an inertial navigation system,
gyroscopes and accelerometers. The navigation system
specific to our system is composed of uFORS-6 fiber optic
gyroscopes and quartz accelerometers. Thus, the thesis
includes detailed description of Allan variance and
calibration tests of each type of inertial sensors. This
work concludes with simulations of different flight
scenarios where the performance of the guidance system and
the effect of the inertial sensor errors are analysed and
discussed. In the balance of this thesis, the effects of
inertial sensor error on position and attitude are also
investigated. Modelling of the individual sensors is
concluded and sources of error in model parameters are
analysed.