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公开(公告)号：US11161602B2
公开(公告)日：2021-11-02
申请号：US16473701
申请日：2017-12-29
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Antonio Zocchi , Massimo Brunetti , Luca Medici , James Wang , Giorgio Lucchi
Abstract: A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element, which is rotatable about a first axis with respect to said stationary support structure with a first rotational speed. The rotor includes at least one blade, which is operatively connected with said rotative element; and a transmission group, which includes an output element rotatable about first axis with a second rotational speed different from first rotational speed.
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公开(公告)号：US12157562B2
公开(公告)日：2024-12-03
申请号：US17788028
申请日：2020-12-23
Applicant: LEONARDO S.P.A.
Inventor： Luca Medici , Stefano Melone
Abstract: A helicopter is described comprising: a tail boom; a fin projecting from the tail boom; and a tailplane arranged at the tail boom and transversal to the fin; at least one of the fin and the tailplane defining a first aerodynamic surface generating a first aerodynamic force; at least one first element transversal to the first aerodynamic surface; and a second aerodynamic surface generating a second aerodynamic force, connected to the first element, facing and spaced from the first aerodynamic surface; the second aerodynamic surface is spaced from the other of the fin and the tailplane.
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公开(公告)号：US20230322400A1
公开(公告)日：2023-10-12
申请号：US18018961
申请日：2021-07-30
Applicant: LEONARDO S.P.A.
Inventor： Luca Medici , Fabio Nannoni , Marco Braghiroli , Andrea Cogliati , Tiziano Frattini , Lorenzo Masellis , Luca Riviello , Alessandro Scola , Marco Tamborini , Matteo Pizzagalli
CPC classification number: B64D31/10 , B64D35/08 , G05D1/0072
Abstract: A method for controlling an aircraft capable of hovering is described, comprising a first engine; a second engine; at least one rotor; and a transmission interposed between the first and second engine and the rotor; the transmission comprises a first and a second inlet connected respectively to a first outlet member of the first engine and to a second outlet member of the second engine; the method comprises step i) of placing the in a first configuration, in which the first and second engine make available a first and a second power value; or in a second configuration, in which the first engine (makes available a third power value greater than the first power value to the first inlet, and the second engine delivers a nil power value to the second inlet; the method also comprises, characterised in that it comprises the steps of ii) detecting a series of parameters associated with the operating conditions of the aircraft; and iii) enabling the transition of the aircraft from the first configuration to the second configuration, when the parameters assume respective first values.
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Patent Agency Ranking
公开(公告)号：USD1041386S1
公开(公告)日：2024-09-10
申请号：US35512933
申请日：2021-05-18
Applicant: LEONARDO S.P.A.
Designer： Stefano Melone , Gabriele Campanardi , Luca Medici , Alessandro Scandroglio , Riccardo Bianco Mengotti
Abstract: 1. Helicopter toy
2. Helicopter toy
1.1 : Perspective
1.2 : Front
1.3 : Side view
1.4 : Rear view
1.5 : Side view
1.6 : Top
1.7 : Bottom
2.1 : Perspective
2.2 : Front
2.3 : Side view
2.4 : Rear view
2.5 : Side view
2.6 : Top
2.7 : Bottom
The translucent gray overlay is provided to represent portions of the Helicopter that are disclaimed. The underlying mechanical parts and the translucent gray overlay itself form no part of the claimed design.-
公开(公告)号：USD1040728S1
公开(公告)日：2024-09-03
申请号：US35512937
申请日：2021-05-18
Applicant: LEONARDO S.P.A.
Designer： Stefano Melone , Gabriele Campanardi , Luca Medici , Alessandro Scandroglio , Riccardo Bianco Mengotti
Abstract: 1. Helicopter
2. Helicopter
1.1 : Perspective
1.2 : Front
1.3 : Side view
1.4 : Rear view
1.5 : Side view
1.6 : Top
1.7 : Bottom
2.1 : Perspective
2.2 : Front
2.3 : Side view
2.4 : Rear view
2.5 : Side view
2.6 : Top
2.7 : Bottom
The translucent gray overlay is provided to represent portions of the helicopter that are disclaimed. The underlying mechanical parts and the translucent gray overlay itself form no part of the claimed design.-
公开(公告)号：US20230174219A1
公开(公告)日：2023-06-08
申请号：US17911544
申请日：2021-03-19
Applicant: LEONARDO S.P.A.
Inventor： Stefano Melone , Gabriele Campanardi , Luca Medici , Alessandro Scandroglio , Riccardo Bianco Mengotti
CPC classification number: B64C5/02 , B64C27/04 , B64C27/82 , B64C2027/8281
Abstract: A helicopter is described comprising a fuselage elongated along a first axis and extending between a nose and a tail boom; a tailplane with a pair of first aerodynamic surfaces elongated along a second axis; the first and second axis define a first plane; the helicopter comprises a pair of elements transversal to the first aerodynamic surfaces; and a pair of second aerodynamic surfaces generating respective second aerodynamic forces, connected to first elements, and facing and spaced from respective first aerodynamic surfaces; each second aerodynamic surface comprises one first root end connected to the respective said element, a second free end spaced from said tail boom, a first leading edge, a first trailing edge opposite to said first leading edge, a first chord at said first root end and a second chord at said second free end parallel to said first axis; the first and the second chord define a second plane tilted with respect to said first plane.
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公开(公告)号：US20230022308A1
公开(公告)日：2023-01-26
申请号：US17788028
申请日：2020-12-23
Applicant: LEONARDO S.P.A.
Inventor： Luca Medici , Stefano Melone
Abstract: A helicopter is described comprising: a tail boom; a fin projecting from the tail boom; and a tailplane arranged at the tail boom and transversal to the fin; at least one of the fin and the tailplane defining a first aerodynamic surface generating a first aerodynamic force; at least one first element transversal to the first aerodynamic surface; and a second aerodynamic surface generating a second aerodynamic force, connected to the first element, facing and spaced from the first aerodynamic surface; the second aerodynamic surface is spaced from the other of the fin and the tailplane.
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公开(公告)号：US11111011B2
公开(公告)日：2021-09-07
申请号：US16474097
申请日：2017-12-29
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Antonio Zocchi , Massimo Brunetti , Luca Medici , James Wang , Giorgio Lucchi
Abstract: A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element which is rotatable about an axis with respect to the stationary support structure. The rotor has at least one blade, which is operatively connected with a rotative element. The rotor has a source of a magnetic field, which is either stationary or driven in rotation at a first rotational speed and an electric conductive element, which is operatively connected to the rotative element and can be driven in rotation at a second rotational speed different from first rotational speed. An electric conductive element is electromagnetically coupled so that an electromotive force is magnetically induced in electric conductive element itself Two rings extend radially inward from a tubular body of the rotor hub with the first ring connected to a plurality of thermally conductive rings of a flow deflector at an axial end of the rotor and the second ring supports the electric conductive element.
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