A convertiplane (1, 1', 1") 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 first lift or negative lift value; - at least one engine operatively connected to said rotors; and - at least one first lifting surface (19, 16) arranged on said tail portion and generating a second lift or negative lift value; 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 (1, 1', 1") between a helicopter configuration and an aeroplane configuration; each said second axis being, in use, transversal to said first axis of said convertiplane (1, 1', 1") in said helicopter configuration and being, in use, substantially parallel to said first axis in said aeroplane configuration; said rotors projecting from said wings from the side of said nose of said fuselage when said convertiplane (1, 1', 1") is in said aeroplane configuration; said rotors being arranged, in use, above said wing when said convertiplane (1, 1', 1") is in said helicopter configuration; said convertiplane (1, 1', 1") landing and taking-off, in use, in said helicopter configuration or in an intermediate configuration between said aeroplane and helicopter configurations; said convertiplane (1, 1', 1") further comprising a pair of canards arranged at said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift or negative lift value; characterised in that each said wing, in turn, comprises: - a first portion, fixed with respect to said fuselage; - a second tip portion, integrally tiltable with the relative said mast about the relative said third axis; and - a third intermediate portion, which is interposed between the respective said first portion and the respective said tip portions; said third intermediate portion of each wing being hinged to said first portion of the respective wing about a fourth axis. - 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 first lift or negative lift value; - at least one engine operatively connected to said rotors; and - at least one first lifting surface (19, 16) arranged on said tail portion and generating a second lift or negative lift value; 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 (1, 1', 1") between a helicopter configuration and an aeroplane configuration; each said second axis being, in use, transversal to said first axis of said convertiplane (1, 1', 1") in said helicopter configuration and being, in use, substantially parallel to said first axis in said aeroplane configuration; said rotors projecting from said wings from the side of said nose of said fuselage when said convertiplane (1, 1', 1") is in said aeroplane configuration; said rotors being arranged, in use, above said wing when said convertiplane (1, 1', 1") is in said helicopter configuration; said convertiplane (1, 1', 1") landing and taking-off, in use, in said helicopter configuration or in an intermediate configuration between said aeroplane and helicopter configurations; said convertiplane (1, 1', 1") further comprising a pair of canards arranged at said nose of said fuselage and defining respective second lifting surfaces adapted to generate a third lift or negative lift value; characterised in that each said wing, in turn, comprises: - a first portion, fixed with respect to said fuselage; - a second tip portion, integrally tiltable with the relative said mast about the relative said third axis; and - a third intermediate portion, which is interposed between the respective said first portion and the respective said tip portions; - a first portion, fixed with respect to said fuselage; - a second tip portion, integrally tiltable with the relative said mast about the relative said third axis; and - a third intermediate portion, which is interposed between the respective said first portion and the respective said tip portions; said third intermediate portion of each wing being hinged to said first portion of the respective wing about a fourth axis.