Design of New Proportional Guidance Law for a Flying Vehicle Using Genetic Algorithm

In this paper, we propose a guidance law for middle and final phases of a medium-range missile the parameters of which are optimized using genetic algorithms. Using a simple proportional guidance law and considering the aerodynamic characteristics of missile the proposed guidance law provides a better performance than proportional experimental guidance. Considering that proportional navigation constants at the time of launching are two factors that play a critical role in hitting the target, in this case, identifying the constant proportional navigation is considered as an optimization problem and it has been tried to set this parameter using a genetic algorithm to obtain the lowest error. Simulation results of six degrees of freedom indicate that the proposed method has a better performance than the other methods.