Rotor state feedback in rotorcraft attitude control

Abstract

An approach to rotor state feedback attitude control aimed at nominal stability, closed-loop performance, uncertainty robustness and tolerance to rotor state feedback faults is proposed. Structured ??? control based on a reduced linearized FlightLab model, an uncertainty description (changes in mass, altitude, center of mass position, speed) and requirements on the sensitivity functions is used to optimize tunings for given controller structures