Patents by Inventor Luigi BOTTASSO
Luigi BOTTASSO has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11760468Abstract: 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.Type: GrantFiled: June 25, 2020Date of Patent: September 19, 2023Assignee: LEONARDO S.P.A.Inventors: Luigi Bottasso, Ermanno Fosco, Paolo Pisani, Francesco Vincenzo, Francesco Rosa, Francesco Braghin, Gabriele Cazzulani, Simone Cinquemani
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Publication number: 20230278703Abstract: 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.Type: ApplicationFiled: May 26, 2021Publication date: September 7, 2023Inventors: Luigi Bottasso, Fabrizio Losi, Alessandro Nava, Sergio Sartori, Roberto Simonetta, Alessandro Airoldi, Matteo Boiocchi
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Patent number: 11738859Abstract: 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.Type: GrantFiled: June 25, 2020Date of Patent: August 29, 2023Assignee: LEONARDO S.P.A.Inventors: Luigi Bottasso, Ermanno Fosco, Paolo Pisani, Francesco Vincenzo, Francesco Rosa, Francesco Braghin, Gabriele Cazzulani, Simone Cinquemani
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Publication number: 20230234701Abstract: A rotor for an aircraft is described, comprising an input shaft rotatable around a first axis; an output member rotatable around a second axis; a coupling element functionally interposed between the input shaft and the output member and adapted to transmit the motion from the input shaft to the output member; the coupling element is configured to allow, in use, a fixed or variable inclination between the respective first and second axes; the coupling element comprises at least a first corrugated element made of an elastically deformable material; the first corrugated element allows the inclination through elastic deformation.Type: ApplicationFiled: May 26, 2021Publication date: July 27, 2023Inventors: Luigi Bottasso, Stefano Poggi, Phil Woody, Fabrizio Losi, Alessandro Nava, Sergio Sartori, Roberto Simonetta, Alessandro Airoldi, Matteo Boiocchi
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Patent number: 11498667Abstract: 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.Type: GrantFiled: October 30, 2018Date of Patent: November 15, 2022Assignee: LEONARDO S.P.A.Inventors: Giuseppe Quaranta, Federico Savorgnan, Pierangelo Masarati, Luigi Bottasso, Attilio Colombo
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Patent number: 11433995Abstract: A kit for a helicopter is described, the helicopter comprising a fuselage and a rotor; the kit comprises at least one device adapted to dampen the vibrations transmitted from the rotor to the fuselage and to be interposed between the fuselage and the rotor; the device, in turn, comprises a first threaded element operatively connectable to the rotor and adapted to, in use, vibrate parallel to a first axis; a second threaded element operatively connectable to the fuselage and operatively connected to the first threaded element so as to, in use, rotationally vibrate about the first axis; and a plurality of threaded rollers, which are screwed on the first and second threaded elements; the rollers being rotatable about their respective second axes parallel to and separate from the first axis with respect to the first and second threaded elements; the rollers are also rotatable about the first axis with respect to the first threaded element and the second threaded element.Type: GrantFiled: June 28, 2019Date of Patent: September 6, 2022Assignee: LEONARDO S.P.A.Inventors: Luigi Bottasso, Attilio Colombo, Pierangelo Masarati, Aykut Tamer, Giuseppe Quaranta
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Publication number: 20220258856Abstract: 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.Type: ApplicationFiled: June 25, 2020Publication date: August 18, 2022Inventors: Luigi Bottasso, Ermanno Fosco, Paolo Pisani, Francesco Vincenzo, Francesco Rosa, Francesco Braghin, Gabriele Cazzulani, Simone Cinquemani
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Publication number: 20220250741Abstract: 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.Type: ApplicationFiled: June 25, 2020Publication date: August 11, 2022Inventors: Luigi Bottasso, Ermanno Fosco, Paolo Pisani, Francesco Vincenzo, Francesco Rosa, Francesco Braghin, Gabriele Cazzulani, Simone Cinquemani
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Patent number: 11319061Abstract: 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.Type: GrantFiled: June 28, 2018Date of Patent: May 3, 2022Assignee: LEONARDO S.P.A.Inventors: Attilio Colombo, Luigi Bottasso, Paolo Pisani, Andrea Favarotto, Dario Colombo, Federico Montagna, Roberto Regonini, Francesco Braghin, Simone Cinquemani
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Patent number: 11247771Abstract: A kit is described that comprises a device adapted to dampen the vibrations transmitted by the rotor to the fuselage; the device comprises two first elements movable along a first axis; two second elements rotatable about the first axis; a first inerter with a first female screw, a first screw, and first rollers rotatable about respective second axes and around the first axis with respect to the first female screw and first screw; a second inerter with a second female screw, a second screw operatively connected to the second female screw; and a plurality of second rollers rotatable about second axes and around the first axis with respect to the second female screw and second screw; the first and second female screws defining the first threaded elements, and the first and second screws defining the second threaded elements; or the first and second screws defining the first threaded elements and the first and second female screws defining the second threaded elements.Type: GrantFiled: June 28, 2019Date of Patent: February 15, 2022Assignee: LEONARDO S.P.A.Inventors: Luigi Bottasso, Attilio Colombo, Pierangelo Masarati, Aykut Tamer, Giuseppe Quaranta
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Patent number: 11161602Abstract: 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.Type: GrantFiled: December 29, 2017Date of Patent: November 2, 2021Assignee: LEONARDO S.P.A.Inventors: Luigi Bottasso, Antonio Zocchi, Massimo Brunetti, Luca Medici, James Wang, Giorgio Lucchi
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Patent number: 11111011Abstract: 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.Type: GrantFiled: December 29, 2017Date of Patent: September 7, 2021Assignee: LEONARDO S.P.A.Inventors: Luigi Bottasso, Antonio Zocchi, Massimo Brunetti, Luca Medici, James Wang, Giorgio Lucchi
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Patent number: 11022100Abstract: A control system for a wind turbine is provided. The wind turbine includes at least one stationary component. The control system includes at least one mechanical load measurement sensor coupled to the at least one stationary component. The system also includes at least one modeling device configured to generate and transmit at least one wind turbine regulation device command signal to at least one wind turbine regulation device to regulate operation of the wind turbine based upon at least one wind inflow parameter.Type: GrantFiled: December 17, 2015Date of Patent: June 1, 2021Assignee: General Electric CompanyInventors: Fabiano Daher Adegas, Sara Simonne L. Delport, Carlo Luigi Bottasso, Stefano Cacciola
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Publication number: 20200391857Abstract: A kit for a helicopter is described, the helicopter comprising a fuselage and a rotor; the kit comprises at least one device adapted to dampen the vibrations transmitted from the rotor to the fuselage and to be interposed between the fuselage and the rotor; the device, in turn, comprises a first threaded element operatively connectable to the rotor and adapted to, in use, vibrate parallel to a first axis; a second threaded element operatively connectable to the fuselage and operatively connected to the first threaded element so as to, in use, rotationally vibrate about the first axis; and a plurality of threaded rollers, which are screwed on the first and second threaded elements; the rollers being rotatable about their respective second axes parallel to and separate from the first axis with respect to the first and second threaded elements; the rollers are also rotatable about the first axis with respect to the first threaded element and the second threaded element.Type: ApplicationFiled: June 28, 2019Publication date: December 17, 2020Inventors: Luigi Bottasso, Attilio Colombo, Pierangelo Masarati, Aykut Tamer, Giuseppe Quaranta
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Publication number: 20200385105Abstract: A kit is described that comprises a device adapted to dampen the vibrations transmitted by the rotor to the fuselage; the device comprises two first elements movable along a first axis; two second elements rotatable about the first axis; a first inerter with a first female screw, a first screw, and first rollers rotatable about respective second axes and around the first axis with respect to the first female screw and first screw; a second inerter with a second female screw, a second screw operatively connected to the second female screw; and a plurality of second rollers rotatable about second axes and around the first axis with respect to the second female screw and second screw; the first and second female screws defining the first threaded elements, and the first and second screws defining the second threaded elements; or the first and second screws defining the first threaded elements and the first and second female screws defining the second threaded elements.Type: ApplicationFiled: June 28, 2019Publication date: December 10, 2020Inventors: Luigi Bottasso, Attilio Colombo, Pierangelo Masarati, Aykut Tamer, Giuseppe Quaranta
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Publication number: 20200298968Abstract: 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.Type: ApplicationFiled: October 30, 2018Publication date: September 24, 2020Inventors: Giuseppe Quaranta, Federico Savorgnan, Pierangelo Masarati, Luigi Bottasso, Attilio Colombo
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Publication number: 20200198779Abstract: 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.Type: ApplicationFiled: June 28, 2018Publication date: June 25, 2020Inventors: Attilio Colombo, Luigi Bottasso, Paolo Pisani, Andrea Favarotto, Dario Colombo, Federico Montagna, Roberto Regonini, Francesco Braghin, Simone Cinquemani
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Publication number: 20200122825Abstract: There is disclosed a rotor for an aircraft capable of hovering, comprising a stationary support structured; a rotative element, which is rotatable about an axis with respect to stationary support structure; at least one blade, which is operatively connected with rotative element; 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 rotative element and can be driven in rotation at a second rotational speed from first rotational speed; electric conductive element is electromagnetically coupled with source, so that an electromotive force is magnetically induced in electric conductive element itself, wherein two rings extend radially inward from a tubular body of the rotor hub, the first ring connecting to a plurality of thermally conductive rings of a flow deflector at an axial end of the rotor, the second ring supporting the electric conductive element.Type: ApplicationFiled: December 29, 2017Publication date: April 23, 2020Inventors: Luigi Bottasso, Antonio Zocchi, Massimo Brunetti, Luca Medici, James Wang, Giorgio Lucchi
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Publication number: 20190352000Abstract: There is disclosed a rotor for an aircraft capable of hovering, comprising: a stationary support structure; a rotative element, which is rotatable about a first axis with respect to said stationary support structure with a first rotational speed; at least one blade, which is operatively connected with said rotative element; and a transmission group, which comprises an output element rotatable about first axis with a second rotational speed different from first rotational speed.Type: ApplicationFiled: December 29, 2017Publication date: November 21, 2019Inventors: Luigi BOTTASSO, Antonio ZOCCHI, Massimo BRUNETTI, Luca MEDICI, James WANG, Giorgio LUCCHI
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Publication number: 20170175709Abstract: A control system for a wind turbine is provided. The wind turbine includes at least one stationary component. The control system includes at least one mechanical load measurement sensor coupled to the at least one stationary component. The system also includes at least one modeling device configured to generate and transmit at least one wind turbine regulation device command signal to at least one wind turbine regulation device to regulate operation of the wind turbine based upon at least one wind inflow parameter.Type: ApplicationFiled: December 17, 2015Publication date: June 22, 2017Inventors: Fabiano Daher Adegas, Sara Simonne L. Delport, Carlo Luigi Bottasso, Stefano Cacciola