This paper describes a novel approach to the design of a control system for an aircraft gas turbine engine. A multi-level multiobjective genetic algorithm is employed to design controllers at both individual operating points using system linearisations and small signal response characteristics, and over the full-flight envelope using a nonlinear model and large signal responses. The proposed approach should allow the selection of smoother controller parameters over the flight envelope and ensure that more consistent control demands are made at off-design operating points.
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