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    ROTOR FOR A HOVER-CAPABLE AIRCRAFT
    7.
    发明公开
    ROTOR FOR A HOVER-CAPABLE AIRCRAFT 审中-公开

    公开(公告)号：EP4269238A3

    公开(公告)日：2023-12-27

    申请号：EP23197448.6

    申请日：2019-07-19

    申请人： Leonardo S.p.a.

    发明人： BOTTASSO, Luigi ,  FOSCO, Ermanno ,  PISANI, Paolo ,  VINCENZO, Francesco ,  ROSA, Francesco ,  BRAGHIN, Francesco ,  CAZZULANI, Gabriele ,  CINQUEMANI, Simone

    IPC分类号： B64C27/00

    摘要： A rotor (3') for an aircraft (1) is described that has a mast (50), an attenuating device (7') to attenuate the transmission of vibrations from the mast (50) in a plane orthogonal to the first axis (A), and a transmission device (15) interposed between the mast (50) and the attenuating device (7'); the attenuating device (7') comprises a first and a second mass unit (8, 9) with a first and a second mass (10, 11) rotatable about the first axis (A) with a first and a second rotational speed ((N-1)*Q; (N+1)*Ω), two control units (40) operable to cause an additional rotation of at least one of the first and second masses (10, 11), and a first and a second support assembly (41, 42) carrying the first and second masses (10, 11); each control unit (40) controls the angle between the first and second masses (10, 11) and comprises a set of drive gear teeth (55') integral with the first support assembly (41, 42), a cogwheel (56) with a set of control gear teeth (57) meshing with the drive gear teeth (55'), and an actuator (58) to cause the rotation of the cogwheel (56) about a second axis (F) and of the first mass (10, 11) about said first axis (A).

    FUSELAGE FOR A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING
    8.
    发明公开
    FUSELAGE FOR A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING 审中-公开

    公开(公告)号：EP4279390A1

    公开(公告)日：2023-11-22

    申请号：EP22174037.6

    申请日：2022-05-18

    申请人： Leonardo S.p.a.

    发明人： MEDICI, Luca ,  BIANCO MENGOTTI, Riccardo ,  BAVETTA, Andrea ,  BASAGLIA, Marco

    IPC分类号： B64D27/24 ,  B64D33/08 ,  B64C29/00 ,  B64C7/00 ,  B64C1/14

    摘要： A fuselage (2, 2', 2") for a convertible aircraft (1) is described, comprising a nose (4) and a tail (5) arranged on mutually opposite sides along a first longitudinal axis (Y) of the fuselage (2); a first portion (100) and a second portion (101) arranged one after the other, proceeding along the first axis (Y) from the nose (4) towards the tail (5); and an electric power source (102) connectable with at least one electric powertrain (40a, 40b, 40c, 40d, 40e, 40f) and arranged inside the second portion (101); the first and second portion (100, 101) define respectively a first and a second section (110, 111, 111") in a plane orthogonal to the first axis (Y); the second section (111) defines at least one air intake (120) that is open towards the outside of the fuselage (2) itself and fluidically connected with the source (102) so as to convey, in use, a flow of cooling air onto the source (102) itself following the forward motion of the aircraft (1); the second section (111, 111") having a larger area than the first section (110); the air intake (120) being arranged at a sidewall (19) of the second portion (101) and externally to the first portion (100) and in a view parallel to the first axis (Y).

    ROTOR FOR A HOVER-CAPABLE AIRCRAFT
    9.
    发明公开
    ROTOR FOR A HOVER-CAPABLE AIRCRAFT 审中-公开

    公开(公告)号：EP4269238A2

    公开(公告)日：2023-11-01

    申请号：EP23197448.6

    申请日：2019-07-19

    申请人： Leonardo S.p.a.

    发明人： BOTTASSO, Luigi ,  FOSCO, Ermanno ,  PISANI, Paolo ,  VINCENZO, Francesco ,  ROSA, Francesco ,  BRAGHIN, Francesco ,  CAZZULANI, Gabriele ,  CINQUEMANI, Simone

    IPC分类号： B64C27/00

    摘要： A rotor (3') for an aircraft (1) is described that has a mast (50), an attenuating device (7') to attenuate the transmission of vibrations from the mast (50) in a plane orthogonal to the first axis (A), and a transmission device (15) interposed between the mast (50) and the attenuating device (7'); the attenuating device (7') comprises a first and a second mass unit (8, 9) with a first and a second mass (10, 11) rotatable about the first axis (A) with a first and a second rotational speed ((N-1)*Q; (N+1)*Ω), two control units (40) operable to cause an additional rotation of at least one of the first and second masses (10, 11), and a first and a second support assembly (41, 42) carrying the first and second masses (10, 11); each control unit (40) controls the angle between the first and second masses (10, 11) and comprises a set of drive gear teeth (55') integral with the first support assembly (41, 42), a cogwheel (56) with a set of control gear teeth (57) meshing with the drive gear teeth (55'), and an actuator (58) to cause the rotation of the cogwheel (56) about a second axis (F) and of the first mass (10, 11) about said first axis (A).