Identification of a Helicopter Dynamic Model for Active Control of Vibrations

Abstract Motivated by the research on active control of helicopter vibrations, in this paper we present a novel dynamic model of the vibrations induced on the fuselage by the blades. The model provides a small-variation relationship between the swash-plate commands and the vertical force at the rotor hub. Based on data obtained from an Agusta Company simulator, the identified model consists of a time-invariant linear dynamic system complemented with periodically time-varying linear and algebraic blocks.