A convertiplane comprising: - a fuselage having a first longitudinal axis and, in turn, comprising a nose and a tail portion; - a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors and generating a lift value; and - a pair of engines operatively connected to said rotors; each said rotor, in turn, comprising a mast rotatable about a second axis; said mast of each said rotor being integrally tiltable with said second axis about a relative third axis transversal to said second axis and with respect to said fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each said second axis being, in use, transversal to said first axis of said convertiplane in said helicopter configuration and being, in use, substantially parallel to said first axis in said aeroplane configuration; said engines being interposed between said rotors along a direction of extension of the relative said wing; wherein each of said engines are of the thermal type; said convertiplane further comprising: - a pair of electric motors operatively connected tc respective said rotors and adapted to drive the rotors in rotation; and - a pair of electric generators electrically connected to respective said electric motors and operatively connected to respective said engines; characterised in that it further comprises an interconnection shaft interposed between said engines and arranged in the said fuselage for the greater part of its length; said electric generators being interposed between said engines along said third axis; each said engine being operatively connected to both said electric generators and being sized so as to provide a level of mechanical power necessary for powering both said electric generators in the event of failure of the other said engine. - a fuselage having a first longitudinal axis and, in turn, comprising a nose and a tail portion; - a pair of wings arranged on respective opposite sides of said fuselage, carrying respective rotors and generating a lift value; and - a pair of engines operatively connected to said rotors; said mast of each said rotor being integrally tiltable with said second axis about a relative third axis transversal to said second axis and with respect to said fuselage, so as to set said convertiplane between a helicopter configuration and an aeroplane configuration; each said second axis being, in use, transversal to said first axis of said convertiplane in said helicopter configuration and being, in use, substantially parallel to said first axis in said aeroplane configuration; said engines being interposed between said rotors along a direction of extension of the relative said wing; wherein each of said engines are of the thermal type; said convertiplane further comprising: - a pair of electric motors operatively connected tc respective said rotors and adapted to drive the rotors in rotation; and - a pair of electric generators electrically connected to respective said electric motors and operatively connected to respective said engines; characterised in that it further comprises an interconnection shaft interposed between said engines and arranged in the said fuselage for the greater part of its length; said electric generators being interposed between said engines along said third axis; each said engine being operatively connected to both said electric generators and being sized so as to provide a level of mechanical power necessary for powering both said electric generators in the event of failure of the other said engine. - a pair of electric motors operatively connected tc respective said rotors and adapted to drive the rotors in rotation; and - a pair of electric generators electrically connected to respective said electric motors and operatively connected to respective said engines; said electric generators being interposed between said engines along said third axis; each said engine being operatively connected to both said electric generators and being sized so as to provide a level of mechanical power necessary for powering both said electric generators in the event of failure of the other said engine.