Guidance and Control of a Two-dimensional Model of a Surface-to-Air Missile Using Proportional, Integral, Derivative and Optimal Fuzzy Control

the missile guidance and control system consists of three subsystems: navigation, guidance, and control. These sub-systems are responsible in the calculation of the deviation of the guided vehicle from the desired path so as to determine the appropriate acceleration command to compensate for the deviation and tracking the acceleration and direction of the missile towards the target. In the usual methods of designing the guidance and control system, each of the guidance and control subsystems is designed separately, assuming ideal subsystem. In the integrated guidance and control approach, the guidance law is developed separately and tested with the assumption of an ideal autopilot. The autopilot is also designed independently and is tested with the assumption of ideal guidance law. This article describes the process of designing and simulating the function of proportional, integral, derivative and optimal fuzzy controller, which is created in order to guide the missile in a two-dimensional problem of minimizing the impact time and the distance to the target. In the optimal fuzzy hybrid controller, Mamdani type fuzzy controller parameters (including input and output membership functions, fuzzy reasoning rules, and input and output gains) are set by solving an optimization problem. Next, the parameters of the proportional-integral-derivative controller of the parallel type are also determined by solving the non-convex optimization problem and it is shown that this type of controller with optimal parameters will provide an optimal guide to the missile.