Patent ID: 11919633
Assignee: LEONARDO S.P.A.
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 0:
1. A convertiplane (1, 1′, 1″) comprising:
a fuselage (2) having a first longitudinal axis (A) and, in turn, comprising a nose (12) and a tail portion (13);
a pair of monoplane wings (3) arranged on respective opposite sides of said fuselage (2), carrying respective rotors (5) and generating a first lift or negative lift value;
at least one engine (4) operatively connected to said rotors (5); and
at least one first lifting surface (19, 16) arranged on said tail portion (13) and generating a second lift or negative lift value;
each said rotor (5), in turn, comprising a mast (9) rotatable about a second axis (B);
said mast (9) of each said rotor (5) being integrally tiltable with said second axis (B) about a relative third axis (E) transversal to said second axis (B) and with respect to said fuselage (2), so as to set said convertiplane (1, 1′, 1″) between a helicopter configuration and an aeroplane configuration;
each said second axis (B) being, in use, transversal to said first axis (A) of said convertiplane (1, 1′, 1″) in said helicopter configuration and being, in use, substantially parallel to said first axis (A) in said aeroplane configuration;
said rotors (5) projecting from said wings (3) from the side of said nose (12) of said fuselage (2) when said convertiplane (1, 1′, 1″) is in said aeroplane configuration;
said rotors (5) being arranged, in use, above said wing (3) 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;
characterised in that it comprises a pair of canards (14) arranged at said nose (12) of said fuselage (2) and defining respective second lifting surfaces adapted to generate a third lift Z or negative lift;
each said wing (3), in turn, comprising:
a first portion (20), fixed with respect to said fuselage (2);
a second tip portion (21), integrally tiltable with the relative said mast (9) about the relative said third axis (E); and
a third intermediate portion (22), which is interposed between the respective said first portion (20) and the respective said tip portions (21).