Abstract: A fuzzy predictive pursuit guidance is proposed as an
alternative to the conventional methods. The purpose of this scheme
is to obtain a stable and fast guidance. The noise effects must be
reduced in homing missile guidance to get an accurate control. An
aerodynamic missile model is simulated first and a fuzzy predictive
pursuit control algorithm is applied to reduce the noise effects. The
performance of this algorithm is compared with the performance of
the classical proportional derivative control. Stability analysis of the
proposed guidance method is performed and compared with the
stability properties of other guidance methods. Simulation results
show that the proposed method provides the satisfying performance.