ولی اله غفاری

The overall goll of this study is to improve guidance system performance of a typical interceptor system and reduce miss distance error, by adding a group of actuators name Attitude Control Motors (ACM) working beside control surfaces, to the guidance system. Management of this system and using algorithm of thrusters for a better performance is important. Attitude Control Motors contain 180 disposable solid rocket motors, installed several angles on first third of lateral body of the interceptor. By burning each one a force produced that the force causes a momentum which rotates the object over it’s center of gravity in the space. By using properly of these rotations, it can be used for attitude control in space. Adding ACM to the guidance system is in order to increase agility and decrease miss distance. In this thesis used computer simulations to analyze the results. Comprehensive researches has been maded on PAC-3 air defense system one of the most prominent interceptor system, for modeling the interceptor. Some of required details have been extracted from related articles and books and some of them obtained from analytical methods and even image adaptation. The body of interceptor has been simulated in Najm program and the 6-DOF model with linearize aerodynamics coefficients by Missile DATCOM codes, has been imported to Simulink of MATLAB. Aerodynamic control subsystem and Attitude Control Motors have been modeled and added to the simulation. For interceptor stability and avoiding of interactions of two control system, a firing management algorithm is needed. Then effective parameters in ACM have been identified and the effect of these parameters on guidance system has been checked.