Fuzzy Logic Based Integrated Guidance and Control Systems for Missiles

Development of an integrated missile flight control system incorporating fuzzy actuator blending logic and a fuzzy guidance system is proposed. Phase I research will be based on a nonlinear dynamic model of the missile incorporating multiple non-collocated actuators. The dynamics of the missile airframe, on-board accelerometer, rate gyro, and the seeker will also be included in the model. An autopilot incorporating fuzzy logic actuator blending logic will developed and evaluated using test inputs. An intelligently maneuvering, high-speed target model will be used in these evaluations. The fuzzy logic autopilot performance will be compared with that of an autopilot designed using nonlinear control theory. Based on the feasibility demonstration in Phase I work, Phase II research will develop the fuzzy logic control and guidance systems for the Navy STANDARD missile using a six degree of freedom missile model. The performance of the fuzzy logic control and guidance system will be compared with those developed using modern control system design methods over the entire operational envelope. Phase III research will implement the fuzzy logic autopilot and guidance systems in flight hardware. Phase III research will also include hardware-in-loop simulation, and fl