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.
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