Comparative analysis of different guidance algorithms for an air to surface missile

In this thesis, it is aimed to compare common guidance laws in literature on a comprehensive missile motion model which two different missile dynamics are used for scenarios with stationary, fixed speed and fixed accelerated target type. Three degree of freedom movement of the missile was modeled by setting a model of the missile including the atmosphere, guidance, autopilot and missile dynamics suitable for operating the aerodynamic database of the desired missile. The aerodynamic database required for aerodynamic forces, moments and autopilot gains has been obtained by Missile DATCOM software according to missile geometry. In order to contribute to the literature, simulations for three different scenarios with seven algorithms selected from acceleration and angle-output algorithms were repeated with two missile geometries and two autopilot models were used in order to operate the model in accordance with acceleration and angle output guidance laws. Pure Proportional Navigation (PPN), True Proportional Navigation (TPN), Augmented Proportional Navigation (APN), Parabolic Homing Guidance (PHG) and Velocity Pursuit Guidance (VPG) as acceleration output guidance laws and Linear Homing Guidance (LHG) and Body Pursuit Guidance (BPG) as angle output guidance laws were compared in terms of flight profiles, flight time, maximum maneuvering value of the missile and target capture performance. Comprehensive analysis study about the guidance laws has been obtained with formation of the comprehensive missile model and evaluation of many criteria. The dependence of the performance of the guidance laws on the target type and missile dynamics was observed according to the results of many simulations performed.