Medium range air defence missile modeling and linearparametric variable guidance and control

In order for a missile to hit its target effectively, it must have a high-performance guidance and autopilot algorithm. Air defense missiles are agile missiles that can reach high speeds and have high maneuverability. Thanks to the effectiveness of guidance algorithms, they minimize the distance between them and the target. In this thesis, autopilot and guidance structures of a canard-controlled air defense missile were designed. First of all, the nonlinear equations of motions of the missile and the mathematical model with 6 degrees of freedom were obtained by the aerodynamic coefficients of the missile taken from the Missile DATCOM program. It was linearized mathematical mpdel around the selected design points. For the linear missile model obtained, the autopilot algorithm was designed based on LQR with the practical suboptimal tracker(PST) method. In order to improve the designed autopilot, the system has been made linear parametric (LPV model) and its performance has been evaluated over the miss distance. True proportional navigation guidance and pursuit guidance, one of the guidance methods in the literature, have been included in the system and their performances have been examined together with the designed autopilots. The designed linear missile model, autopilot and guidance algorithms were simulated using MATLAB/Simulink application. As a result of the simulation studies, better performance autopilot and guidance algorithms were determined and information was given about how to develop better in the future.