Abstract
In this paper, a multi-objective optimization-based methodology for rotorcraft attitude control law design is applied to a tilt-rotor case; the framework allows to enforce requirements of stability, performance, control action moderation, and safety. The structured H∞ approach is taken into account, and the optimization problem is stated as a mixed-sensitivity problem. Rotor state feedback is used to limit flap motion, and is introduced as an additional loop to a classical attitude control law.
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