Simulation for Signals of Modern Missiles Guidance Commands

Abstract

Nowadays, the increasing developments in applied mathematics and computational capabilities simplify the design and implementation of control theory. In addition, the increasing developments in embedded systems and its availability in the civilian market with low cost, size, and weight attract the researchers all over the world towards embedded flight control systems. The guided missiles, especially the air to air guided missiles, are one of the most important real applications which are widely used nowadays in almost all the modern combats. The present work is concerned with modeling and simulation for signals of an air to air guided missile via four steps. The first, modeling each module of the missile such as seeker, guidance loop, aerodynamics, autopilot and the equations of motion. The second, improving the autopilot design for better interception results. The third, designing an advanced controller in order to be compared to the classical one for better results. The fourth, implementation of the best controller on an Arduino UNO system to validate a processor-in-loop (PIL) experimental test. Toward the objective of the thesis, the motion equations are derived clarifying the aerodynamic coefficients. The solution of these equations is described in a modular form programmed within MATLAB/SIMULINK environments to form the baseline for the subsequent design and analysis. System identification is carried out to represent the controlled plant by the autopilot. Then, the simulation is tested with different tactical scenarios to verify the missile model robustness. The simulation results are validated by the interception state and the control effort exerted by the missile autopilot which is translated to the form of actuator effort and a variation in the incidence angle of the missile. Next, the proposed model performance is improved by designing a more robust autopilot that succeeded to overcome the uncertainties of the first autopilot during the missile flight. Also, an advanced fuzzy controller is carried out during the simulation to compare the missile performance and its flight characteristics using both classical and advanced controllers. Finally, the selected autopilot is implemented on an Arduino UNO system to verify the designed controller on hardware. The verification step is carried out via a processor-in-loop (PIL) experimental test.