Patent ID: 6367736
Filing Date: 2002-04-09
Classification: B64C,B64D

Abstract:
A convertiplane (1) comprising:a fuselage (2); a wing (4) having a central portion (5) fixed to said fuselage (2), and two half-wings (6), projecting from said fuselage (2); two rotors (11) carried by respective supporting structures (9) at opposite ends of the half wings (6), and having respective shafts (12); two engines (20) fixed to respective said half-wings (6) by respective supporting means (23, 24); transmission means (25) connecting each of said rotors (11) to both said engines (20); and means (7, 48) for changing the position of said rotors (11) between a helicopter mode wherein said shafts (12) of said rotors (11) are substantially vertical; and an airplane mode wherein said shafts (12) of said rotors (11) are substantially horizontal; wherein said means (7, 48) for changing the position of said rotors (11) comprising a beam element (7) extending the full length of the wing (4), rotating about a respective axis (A), and rigidly interconnecting said supporting structures (9) of said rotors (11); and first actuating means (48) for rotating said beam element (7) about said axis (A); said half-wings comprising respective fixed portions (13) adjacent to said fuselage (2), and respective movable portions (14) located between said fixed portions (13) and the respective supporting structures (9) of said rotors (11) and rotatable about said beam element (7); said convertiplane (1) comprising second actuating means (55) for rotating said movable portions (14) with respect to said fixed portions (13) and to said beam element (7).