ROTORCRAFT FITTED WITH AN ANTIVIBRATION SYSTEM , AND A METHOD OF ADJUSTING SUCH AN ANTIVIBRATION SYSTEM

Abstract

A rotorcraft having an antivibration system , the antivibration system being arranged at the interface between a fuselage of the rotorcraft and a casing of a main power transmission gearbox , or " MGB ” , in order to transmit rotary motion generated by an engine of the rotorcraft to a main rotor providing the rotorcraft at least with lift , and possibly also propulsion , the antivibration system including calculation means for analyzing as a function of time the dynamic excitation and the resulting vibration transmitted to the fuselage of the rotorcraft