Patents by Inventor Attilio Colombo
Attilio Colombo 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: 11866159Abstract: A rotor for a hover-capable aircraft includes an attenuating device to attenuate the transmission of vibrations from a mast to the aircraft. The attenuating device includes a first mass free to oscillate parallel to a hub rotation axis with respect to a casing of the attenuating device and elastically connected to the casing. The attenuating device further includes a second mass free to oscillate parallel to the hub rotation axis, connection means adapted to make the first and second masses integrally movable along the hub rotation axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.Type: GrantFiled: May 26, 2020Date of Patent: January 9, 2024Assignee: LEONARDO S.P.A.Inventors: Attilio Colombo, Gabriele Cazzulani, Simone Cinquemani, Ferruccio Resta, Francesco Braghin
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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: 20220258855Abstract: A rotor for a hover-capable aircraft is described that comprises: a hub rotating about an axis and, in turn, comprising a plurality of blades, a mast connectable to a power unit of the aircraft and operatively connected to the hub to drive the hub in rotation about said axis, and an attenuating device to attenuate the transmission of vibrations from the mast to the aircraft parallel to said; the attenuating device, in turn, comprising a casing, a first mass free to oscillate parallel to said axis with respect to the casing and elastically connected to the casing, a second mass free to oscillate parallel to said axis, connection means adapted to make the first and second masses integrally movable along said axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.Type: ApplicationFiled: May 26, 2020Publication date: August 18, 2022Inventors: Attilio Colombo, Gabriele Cazzulani, Simone Cinquemani, Ferruccio Resta, Francesco Braghin
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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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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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Patent number: 10793263Abstract: A rotor for a hover-capable aircraft is described that comprises: a drive mast; a hub operatively connected to the drive mast and rotatable about a first axis; and at least two blades hinged to the hub, via a rigid or elastically deformable connection, so as to be able to assume an attitude rotated about and/or translated along at least a second axis with respect to said hub; the aircraft further comprising sensor means configured to detect the attitude of at least one said blade with respect to the hub; the sensor means are configured to acquire an optical image associated with the attitude of the blade with respect to the hub.Type: GrantFiled: April 7, 2017Date of Patent: October 6, 2020Assignee: LEONARDO S.P.A.Inventors: Matteo Redaelli, Luca Riviello, Attilio Colombo, Lorenzo Trainelli, Emanuele Zappa, Alberto Rolando, Potito Cordisco, Edoardo Vigoni, Mauro Terraneo, Riccardo Grassetti
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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: 20190112038Abstract: A rotor for a hover-capable aircraft is described that comprises: a drive mast; a hub operatively connected to the drive mast and rotatable about a first axis; and at least two blades hinged to the hub, via a rigid or elastically deformable connection, so as to be able to assume an attitude rotated about and/or translated along at least a second axis with respect to said hub; the aircraft further comprising sensor means configured to detect the attitude of at least one said blade with respect to the hub; the sensor means are configured to acquire an optical image associated with the attitude of the blade with respect to the hub.Type: ApplicationFiled: April 7, 2017Publication date: April 18, 2019Inventors: Matteo Redaelli, Luca Riviello, Attilio Colombo, Lorenzo Trainelli, Emanuele Zappa, Alberto Rolando, Potito Cordisco, Edoardo Vigoni, Mauro Terraneo, Riccardo Grassetti
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Patent number: 9995168Abstract: A hover aircraft rotor having a hub which rotates about an axis and has a number of blades; a drive shaft connectable to a drive member of the aircraft and connected functionally to the hub to rotate the hub about the axis; and damping means for damping vibration transmitted to the shaft, and which include a mass designed to oscillate, in use, to oppose transmission to the shaft of vibration generated by rotation of the blades; the mass being free to oscillate parallel to the axis, to oppose transmission to the shaft of vibration having main components along the axis.Type: GrantFiled: October 1, 2014Date of Patent: June 12, 2018Assignee: AGUSTAWESTLAND S.P.A.Inventor: Attilio Colombo
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Publication number: 20150098801Abstract: A hover aircraft rotor having a hub which rotates about an axis and has a number of blades; a drive shaft connectable to a drive member of the aircraft and connected functionally to the hub to rotate the hub about the axis; and damping means for damping vibration transmitted to the shaft, and which include a mass designed to oscillate, in use, to oppose transmission to the shaft of vibration generated by rotation of the blades; the mass being free to oscillate parallel to the axis, to oppose transmission to the shaft of vibration having main components along the axis.Type: ApplicationFiled: October 1, 2014Publication date: April 9, 2015Inventor: Attilio COLOMBO
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Patent number: 8496435Abstract: A rotor for a helicopter, having a drive shaft rotating about a first axis; a hub angularly integral with the drive shaft about the first axis; and at least two blades projecting from the hub on opposite sides of the first axis and elongated along respective second axes crosswise to the first axis; each blade is movable with respect to the hub and to the other blade about a respective third axis crosswise to the respective second axis; the rotor has at least two dampers for damping oscillation of respective blades about the respective third axes, and which have respective first portions movable integrally with the respective blades about the respective third axes; and the dampers have respective second portions connected elastically to the respective first portions and functionally to each other.Type: GrantFiled: February 23, 2010Date of Patent: July 30, 2013Assignee: Agusta S.p.A.Inventors: Fabio Nannoni, Dante Ballerio, Pierre Abdel Nour, Attilio Colombo
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Patent number: 8141813Abstract: A helicopter having a rotor, a fuselage, and a transmission connected functionally to the rotor; the helicopter has a supporting body supporting at least the transmission, and connecting means having a first connecting member and at least one second connecting member connected to the supporting body and the fuselage respectively; and the connecting means have elastic means interposed between the first and second connecting member.Type: GrantFiled: October 19, 2009Date of Patent: March 27, 2012Assignee: Agusta S.p.A.Inventors: Santino Pancotti, Dante Ballerio, Attilio Colombo
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Patent number: 7857255Abstract: A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means.Type: GrantFiled: May 15, 2006Date of Patent: December 28, 2010Assignee: Agusto S.p.A.Inventors: Santino Pancotti, Attilio Colombo
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Publication number: 20100215496Abstract: A rotor for a helicopter, having a drive shaft rotating about a first axis; a hub angularly integral with the drive shaft about the first axis; and at least two blades projecting from the hub on opposite sides of the first axis and elongated along respective second axes crosswise to the first axis; each blade is movable with respect to the hub and to the other blade about a respective third axis crosswise to the respective second axis; the rotor has at least two dampers for damping oscillation of respective blades about the respective third axes, and which have respective first portions movable integrally with the respective blades about the respective third axes; and the dampers have respective second portions connected elastically to the respective first portions and functionally to each other.Type: ApplicationFiled: February 23, 2010Publication date: August 26, 2010Inventors: Fabio Nannoni, Dante Ballerio, Pierre Abdel Nour, Attilio Colombo
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Publication number: 20100096492Abstract: A helicopter having a rotor, a fuselage, and a transmission connected functionally to the rotor; the helicopter has a supporting body supporting at least the transmission, and connecting means having a first connecting member and at least one second connecting member connected to the supporting body and the fuselage respectively; and the connecting means have elastic means interposed between the first and second connecting member.Type: ApplicationFiled: October 19, 2009Publication date: April 22, 2010Inventors: Santino Pancotti, Dante Ballerio, Attilio Colombo
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Publication number: 20090321556Abstract: A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means.Type: ApplicationFiled: May 15, 2006Publication date: December 31, 2009Applicant: AGUSTA S.p.A.Inventors: Santino Pancotti, Attilio Colombo