Patent ID: 7582032

Claim:
An antivibration device configured for an airframe or a helicopter, comprising: at least two sets ( 2 , 3 ) each comprising two identical rotors ( 4 , 5 ; 6 , 7 ) having respective eccentric flyweights ( 4 A, 5 A; 6 A, 7 A), said sets being disposed symmetrically about an axis of symmetry, and axes of rotation of said rotors being parallel to one another and orthogonal to said axis of symmetry; a drive system ( 8 ) for setting said rotors into rotation; controllable moving equipment ( 11 ) carrying said drive system ( 8 ) and capable of sliding along said axis of symmetry to vary a phase offset between the eccentric flyweight rotors of the sets, the phase offset being a function of a vibration that needs to be absorbed, said drive system ( 8 ) comprising a single motor ( 12 ) for rotating said rotors, having its axis disposed perpendicularly to said axis of symmetry, and driving an endless connection passing around said rotors ( 4 , 5 ; 6 , 7 ) so that a plurality of lengths of strands of the connection passing through said sets are equal, wherein the antivibration device is fitted to the airframe or the helicopter.