Patent attributes
A convertiplane is described that comprises a fuselage, having a first longitudinal axis, with a nose and a tail portion; a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors; a pair of engines operatively connected to respective said rotors; at least one first lifting surface arranged on said tail portion; and a pair of canards arranged on said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor comprising a mast rotatable about a second axis and about an relative third axis transversal to said second axis and with respect to the fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each second axis, in use, being transversal to the first axis of said convertiplane in said helicopter configuration and being parallel to said first axis in said aeroplane configuration.
