Patent ID: 8777150

Claim:
A convertiplane ( 1 ) comprising: a pair of semi-wings ( 3 ); a first and a second rotor ( 4 ) which may rotate about relative first axes (B) and tilt about relative second axes (C) together with said first axes (B) with respect to said semi-wings ( 3 ) between a helicopter mode and an aeroplane mode; said first axis (B) being, in use, transversal to a longitudinal direction (A) of said convertiplane ( 1 ) in said helicopter mode, and being, in use, substantially parallel to said longitudinal direction (A) in said aeroplane mode; said first and second rotor ( 4 ) being tiltable about relative second axes (C) independently of each other; said convertiplane ( 1 ) further comprising: a first actuator ( 52 ) operatively connected to said first rotor ( 4 ) and adapted to tilt said first rotor ( 4 ) about a relative second axis (C); a second actuator ( 52 ) operatively connected to said second rotor ( 4 ) and adapted to tilt said second rotor ( 4 ) about a relative second axis (C); and a flight control system ( 49 ) adapted to control first and second actuators ( 52 ) independently of each other; each said first and second actuator ( 50 , 52 ) comprising: a control unit ( 51 ) controlled, in turn, by said flight control system ( 49 ) on the basis of a plurality of flight and mission parameters; a fixed part ( 53 ); a piston ( 54 ) slidable relative to said fixed part ( 53 ) and controlled, in use, by said control unit ( 51 ); and a rod ( 55 ) which may rotate about a relative said second axis (C), is hinged to said piston ( 54 ), and is connected to said relative first and second rotor ( 4 ), so as to cause the tilting of said first and second rotor ( 4 ) about relative second axis (C).