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公开(公告)号：US20230278703A1
公开(公告)日：2023-09-07
申请号：US18008355
申请日：2021-05-26
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Fabrizio Losi , Alessandro Nava , Sergio Sartori , Roberto Simonetta , Alessandro Airoldi , Matteo Boiocchi
CPC classification number: B64C27/14 , B64C27/06 , F16D3/845 , F16D2200/006
Abstract: A helicopter is described comprising a motor member comprising an output shaft and a first stator rotatably supporting the output shaft around a first axis; a main rotor adapted to provide the lift necessary for the support and the thrust necessary for the movement of the helicopter; a transmission interposed between the motor member and the main rotor; the transmission comprises, in turn, an input shaft rotatable around a second axis and a second stator rotatably supporting the input shaft around the second axis; the helicopter also comprises a joint interposed between the first and second stator, angularly fixed with respect to the first axis, and configured to allow an inclination between the first and second stator in a plane parallel to said first axis; the joint comprises a first corrugated element made of an elastically deformable material, interposed between said first and second stator, and adapted to allow the inclination through elastic deformation.
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公开(公告)号：US20220258856A1
公开(公告)日：2022-08-18
申请号：US17627462
申请日：2020-06-25
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Ermanno Fosco , Paolo Pisani , Francesco Vincenzo , Francesco Rosa , Francesco Braghin , Gabriele Cazzulani , Simone Cinquemani
IPC: B64C27/00
Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.
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公开(公告)号：US11738859B2
公开(公告)日：2023-08-29
申请号：US17627462
申请日：2020-06-25
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Ermanno Fosco , Paolo Pisani , Francesco Vincenzo , Francesco Rosa , Francesco Braghin , Gabriele Cazzulani , Simone Cinquemani
IPC: B64C27/00
CPC classification number: B64C27/001 , B64C2027/003 , B64C2027/004 , B64C2027/005
Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.
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公开(公告)号：US11319061B2
公开(公告)日：2022-05-03
申请号：US16621178
申请日：2018-06-28
Applicant: LEONARDO S.P.A.
Inventor： Attilio Colombo , Luigi Bottasso , Paolo Pisani , Andrea Favarotto , Dario Colombo , Federico Montagna , Roberto Regonini , Francesco Braghin , Simone Cinquemani
Abstract: A rotor for an aircraft is described that comprises: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.
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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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Patent Agency Ranking
公开(公告)号：US12054246B2
公开(公告)日：2024-08-06
申请号：US18008355
申请日：2021-05-26
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Fabrizio Losi , Alessandro Nava , Sergio Sartori , Roberto Simonetta , Alessandro Airoldi , Matteo Boiocchi
IPC: B64C27/12
CPC classification number: B64C27/12 , F16D2200/006
Abstract: A helicopter is described comprising a motor member comprising an output shaft and a first stator rotatably supporting the output shaft around a first axis; a main rotor adapted to provide the lift necessary for the support and the thrust necessary for the movement of the helicopter; a transmission interposed between the motor member and the main rotor; the transmission rotatable around a second axis and a second stator rotatably supporting the input shaft around the second axis; the helicopter also comprises a joint interposed between the first and second stator, angularly fixed with respect to the first axis, and configured to allow an inclination between the first and second stator in a plane parallel to said first axis; the joint comprises a first corrugated element made of an elastically deformable material, interposed between said first and second stator, and adapted to allow the inclination through elastic deformation.
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公开(公告)号：US11760468B2
公开(公告)日：2023-09-19
申请号：US17627445
申请日：2020-06-25
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Ermanno Fosco , Paolo Pisani , Francesco Vincenzo , Francesco Rosa , Francesco Braghin , Gabriele Cazzulani , Simone Cinquemani
IPC: B64C27/00
CPC classification number: B64C27/001 , B64C2027/003 , B64C2027/004 , B64C2027/005
Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis; and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses; and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and each control unit comprises: a belt coupled to the support assembly and a drive unit coupled to the first belt, to cause the rotation of the first support assembly with respect to said transmission device.
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公开(公告)号：US11498667B2
公开(公告)日：2022-11-15
申请号：US16754270
申请日：2018-10-30
Applicant: LEONARDO S.P.A.
Inventor： Giuseppe Quaranta , Federico Savorgnan , Pierangelo Masarati , Luigi Bottasso , Attilio Colombo
IPC: B64C27/00
Abstract: A rotor for a hover-capable aircraft is described, comprising: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and operatively connected to the hub to drive the hub in rotation about the axis; and damping means for damping vibrations transmitted to the mast, which comprise a mass designed to oscillate in a plane transversal to the axis so as to contain flexural vibrations of the mast generated by rotation of the blades; the damping means also comprise elastic means having a desired stiffness along the axis and operatively connected to the mass to contain vibration of the mast along the axis.
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公开(公告)号：US20220250741A1
公开(公告)日：2022-08-11
申请号：US17627445
申请日：2020-06-25
Applicant: LEONARDO S.P.A.
Inventor： Luigi Bottasso , Ermanno Fosco , Paolo Pisani , Francesco Vincenzo , Francesco Rosa , Francesco Braghin , Gabriele Cazzulani , Simone Cinquemani
IPC: B64C27/00
Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis; and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and each control unit comprises: a belt coupled to the support assembly and a drive unit coupled to the first belt, to cause the rotation of the first support assembly with respect to said transmission device.
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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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