Patent ID: 7857255
Filing Date: 2010-12-28
Classification: B64C

Abstract:
1. A helicopter comprising a rotor, a fuselage connected to said rotor by connecting means, and a control device for controlling vibration of said fuselage; said control device comprising generating means for generating signals associated with vibration of said fuselage, and actuating means for producing a force on said fuselage associated with said signals to reduce said vibration; said connecting means comprising at least one stationary rod extending along an axis and being connected, at opposite ends with respect to said axis, to said rotor and to said fuselage; said actuating means comprising at least one actuator connected to said rod; characterized in that said actuator exchanges forces with and is connected to said rod at only one section crosswise to said axis; said actuator comprising: said connecting means comprising only one plate which is connected to said shell and to said rod; said shell being connected to and exchanging forces with said rod at said only one section.