Applications of fuzzy logic: towards high machine intelligence quotient systems
Applications of fuzzy logic: towards high machine intelligence quotient systems
Development of an automated fuzzy-logic-based expert system for unmanned landing
Fuzzy Sets and Systems
Genetic Algorithms and Fuzzy Logic Systems: Soft Computing Perspectives
Genetic Algorithms and Fuzzy Logic Systems: Soft Computing Perspectives
WSEAS Transactions on Systems and Control
A direct adaptive neural command controller design for an unstable helicopter
Engineering Applications of Artificial Intelligence
Fuzzy control of the position for the piston of an industrial robot
ICS'08 Proceedings of the 12th WSEAS international conference on Systems
Real-time, embedded fuzzy control of the pioneer3-DX robot for path following
ICS'08 Proceedings of the 12th WSEAS international conference on Systems
WSEAS Transactions on Systems and Control
Neuro-controller design for nonlinear fighter aircraft maneuver using fully tuned RBF networks
Automatica (Journal of IFAC)
Aircrafts' control and command using hierarchical dynamic inversion
WSEAS Transactions on Systems and Control
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Aircraft dynamics are in general nonlinear, time varying, and uncertain. A control system (classical control systems) designed for a flight condition, may not provide the desired stability and performance characteristics in case of deviation from the equilibrium point. There are numerous studies regarding flight control in the literature. One of them is fuzzy flight control system. Fuzzy logic controllers (FLCs) from their inception have demonstrated a vast range of applicability to processes where the plant transfer function is not defined but the control action can be described in terms of linguistic variables. FLC's are also being used with improved performance instead of "classical" controllers where the plant transfer function is known. Most of the applications about the design of fuzzy flight control are in simulation level. In this study, the design of fuzzy and classical PD controller for the pitch rate damping system is analyzed and the results for a two-engined jet fighter aircraft are evaluated in a MATLAB coded program.