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公开(公告)号：US20220106031A1
公开(公告)日：2022-04-07
申请号：US17312286
申请日：2019-10-31
申请人： LEONARDO S.P.A.
发明人： Pierre Abdel Nour , Matteo Pecoraro
摘要： An aircraft is described that comprises: a fuselage with a first axis of longitudinal extension; and a tail portion arranged at a tail end of the fuselage; the tail portion comprises two surfaces arranged in a V-shape, inclined to each other and symmetrical with respect to the first axis; each surface comprises an associated winglet arranged transversely with respect to the surface and fixed with respect to the surface.
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2.发明申请公开(公告)号：US20180037335A1
公开(公告)日：2018-02-08
申请号：US15555928
申请日：2016-03-11
申请人： LEONARDO S.p.A.
发明人： Pierre Abdel Nour , Paolo Brughera , Fabio Monti
摘要： A display device for displaying the attitude of an aircraft with respect to a fixed direction in space is described, said device comprising: a first element that can be fastened to the aircraft; and a second element, which is free to move with respect to the first element, following a change in position of first element with respect to the fixed direction; the second element in turn comprising: a mass, which is designed to return the second element to the same stable position with respect to the fixed direction when the first element changes its position with respect to the fixed direction; and a visual indication, which is representative of the position of the fixed direction, as the position of the first element changes.
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公开(公告)号：US11472543B2
公开(公告)日：2022-10-18
申请号：US16769142
申请日：2018-12-27
申请人： LEONARDO S.P.A.
摘要： A convertiplane is described that has a fuselage with a first axis, a pair of half-wings, and a pair of rotors arranged on mutually opposite ends of the half-wings. The rotor comprises a mast hinged on a second axis and a plurality of blades hinged on the mast. The mast of the rotor can be tilted with the second axis about a third axis transversal to the second axis and with respect to the fuselage to transform the convertiplane between a helicopter mode and an aeroplane mode; the second axis is transversal to the first axis in the helicopter mode and is parallel to the first axis in the aeroplane mode. The rotor disc can be tilted about a fourth axis. The rotor comprises control means for controlling the cyclic pitch and collective pitch of the blades comprising: a first actuator controllable to vary the collective pitch, a second actuator controllable to vary the tilt of the rotor disc about the fourth axis and a rod movable to alter the tilt of the corresponding rotor disc about a fifth axis according to the mode of the convertiplane.
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公开(公告)号：US20220073202A1
公开(公告)日：2022-03-10
申请号：US17416091
申请日：2019-10-31
申请人： LEONARDO S.P.A.
摘要： Convertiplane comprising a fuselage; a pair of wings, a pair of nacelles fixed with respect to the wings, and a pair of rotors rotatable about respective second axes and tiltable about a third axis between a first position, reached when the convertiplane is in an aeroplane configuration, and a second position, reached when the convertiplane is in a helicopter configuration. The wing comprises a wing box and a first appendage movable when the convertiplane is in the aeroplane configuration, between a first neutral position, a second raised operating position, and a third lowered operating position; the wing comprises a second appendage movable between a first neutral position assumed when the convertiplane is in the aeroplane configuration and in which it defines an extension of the wing box, and a second position assumed when the convertiplane is in the helicopter configuration and in which it defines, with the wing box, an opening through which the downwash generated by the rotor can flow.
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公开(公告)号：US10435172B2
公开(公告)日：2019-10-08
申请号：US15555928
申请日：2016-03-11
申请人： LEONARDO S.p.A.
发明人： Pierre Abdel Nour , Paolo Brughera , Fabio Monti
摘要： A display device for displaying the attitude of an aircraft with respect to a fixed direction in space is described, said device comprising: a first element that can be fastened to the aircraft; and a second element, which is free to move with respect to the first element, following a change in position of first element with respect to the fixed direction; the second element in turn comprising: a mass, which is designed to return the second element to the same stable position with respect to the fixed direction when the first element changes its position with respect to the fixed direction; and a visual indication, which is representative of the position of the fixed direction, as the position of the first element changes.
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6.发明公开公开(公告)号：US20240051678A1
公开(公告)日：2024-02-15
申请号：US18267626
申请日：2021-11-30
申请人： LEONARDO S.P.A.
发明人： Vincenzo Taumaturgo , Pierre Abdel Nour , Isidoro Piccolini , Clemente Brena , Simone Gobbi , Gianfranco Cito
CPC分类号： B64D45/00 , B64D43/00 , B64C29/0033
摘要： It is disclosed an indicator for an aircraft capable of hovering, comprising a first indication associated to the value of vertical speed of the aircraft itself; the indicator comprises a first area wherein a second indication can be displayed that is associated to a Vortex Ring State condition being reached.
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7.发明授权公开(公告)号：US11891165B2
公开(公告)日：2024-02-06
申请号：US17312286
申请日：2019-10-31
申请人： LEONARDO S.P.A.
发明人： Pierre Abdel Nour , Matteo Pecoraro
CPC分类号： B64C23/069 , B64C29/0033
摘要： An aircraft is described that comprises: a fuselage with a first axis of longitudinal extension; and a tail portion arranged at a tail end of the fuselage; the tail portion comprises two surfaces arranged in a V-shape, inclined to each other and symmetrical with respect to the first axis; each surface comprises an associated winglet arranged transversely with respect to the surface and fixed with respect to the surface.
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公开(公告)号：US11834168B2
公开(公告)日：2023-12-05
申请号：US17416091
申请日：2019-10-31
申请人： LEONARDO S.P.A.
CPC分类号： B64C29/0033 , B64C9/04 , B64C9/18 , B64C2009/005
摘要： Convertiplane comprising a fuselage; a pair of wings, a pair of nacelles fixed with respect to the wings, and a pair of rotors rotatable about respective second axes and tiltable about a third axis between a first position, reached when the convertiplane is in an aeroplane configuration, and a second position, reached when the convertiplane is in a helicopter configuration. The wing comprises a wing box and a first appendage movable when the convertiplane is in the aeroplane configuration, between a first neutral position, a second raised operating position, and a third lowered operating position; the wing comprises a second appendage movable between a first neutral position assumed when the convertiplane is in the aeroplane configuration and in which it defines an extension of the wing box, and a second position assumed when the convertiplane is in the helicopter configuration and in which it defines, with the wing box, an opening through which the downwash generated by the rotor can flow.
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公开(公告)号：US20220073185A1
公开(公告)日：2022-03-10
申请号：US17416115
申请日：2019-10-31
申请人： LEONARDO S.P.A.
摘要： A wing having a wing box (20) defining a first wing profile with a first leading edge, a first trailing edge, a first top surface and a first bottom surface; a first appendage hinged on the wing box and defining a second wing profile, in turn comprising an end wall and a second trailing edge, a second top surface and a second bottom surface; the first appendage is movable between: a first position, in which the first and the second wing profiles are contiguous with each other and a second position, in which the second bottom surface and second top surface are respectively separated from the first bottom surface and first top surface; the wing box comprises a first spar having a curved section in a plane orthogonal to the associated first axis; the end wall is curved and arranged abutting against the first spar at least along the second top surface and the second bottom surface when the first movable appendage is in the first position.
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公开(公告)号：US20210221496A1
公开(公告)日：2021-07-22
申请号：US16769142
申请日：2018-12-27
申请人： LEONARDO S.P.A.
摘要： A convertiplane is described that has a fuselage with a first axis, a pair of half-wings, and a pair of rotors arranged on mutually opposite ends of the half-wings. The rotor comprises a mast hinged on a second axis and a plurality of blades hinged on the mast. The mast of the rotor can be tilted with the second axis about a third axis transversal to the second axis and with respect to the fuselage to transform the convertiplane between a helicopter mode and an aeroplane mode; the second axis is transversal to the first axis in the helicopter mode and is parallel to the first axis in the aeroplane mode. The rotor disc can be tilted about a fourth axis. The rotor comprises control means for controlling the cyclic pitch and collective pitch of the blades comprising: a first actuator controllable to vary the collective pitch, a second actuator controllable to vary the tilt of the rotor disc about the fourth axis and a rod movable to alter the tilt of the corresponding rotor disc about a fifth axis according to the mode of the convertiplane.
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