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.