A novel approach to guidance and control system design using genetic-based fuzzy logic model

The proportional navigation guidance law usually guides traditional aerodynamically controlled missiles in the terminal phase. Such design approaches possess little flexibility on the improvement of engagement performance robustness. The Takagi-Sugeno (T-S) fuzzy logic theory and the gain scheduling technique are presented to design guidance and control (GC) parameters over coupled flight conditions. A genetic algorithm also serves as the computing device to determine the consequent function parameters of the fuzzy rules. The proposed design paradigm offers a way to implement simple but robust solutions that cover a wide range of aerodynamic variations. Complete simulation results illustrate the engagement performance and applicability of this design