Patents by Inventor Pascal Pome
Pascal Pome 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: 11878806Abstract: A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.Type: GrantFiled: May 2, 2022Date of Patent: January 23, 2024Assignee: Airbus Operations SASInventors: Pascal Pome, Lionel Czapla, Benjamin Thubert
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Patent number: 11866185Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.Type: GrantFiled: March 23, 2022Date of Patent: January 9, 2024Assignees: AIRBUS SAS, AIRBUS OPERATIONS SASInventors: Christophe Labarthe, Franck Alvarez, Fabien Latourelle, Olivier Verseux, Pascal Pome, Jean Francois Allias, Olivier Ciet, Olivier Raspati, Anthony Roux, Benedikt Bammer
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Publication number: 20230415906Abstract: An aircraft propulsion assembly including at least one first support that supports an electric propulsion system, at least one first attachment configured to connect the first support and a support structure of an aircraft, at least one second support distinct from and dissociated from the first support supporting a source of electrical energy configured to supply the electric propulsion system with electrical energy, as well as at least one second attachment configured to connect the second support and the support structure. An aircraft may include at least one such propulsion assembly. Given that the second support is distinct from and dissociated from the first support system, vibrations generated by the electric propulsion system are not transmitted to the source of electrical energy.Type: ApplicationFiled: June 21, 2023Publication date: December 28, 2023Inventors: Kotaro FUKASAKU, Rémi AMARGIER, Lionel CZAPLA, Nicolas JOLIVET, Pascal POME
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Patent number: 11661181Abstract: An aircraft having a fuselage having a pressurized upper space above the floor and a lower space beneath the floor, a wing, a hollow support stay fixed between the lower space level of the fuselage and the wing, an electric motor propeller propulsion system fixed beneath each wing, the output shaft of the motor driving a propeller in rotation, a production system having a fuel cell producing electrical energy supplying the electric motor with electricity via electrical conductors, a hydrogen reservoir fixed in the lower space, and a hydrogen inlet pipe feeding hydrogen from a hydrogen reservoir to the production system, wherein the hydrogen inlet pipe extends through the interior of the support stay. The electrical conductors or the hydrogen pipes pass through the stays on the outside of the fuselage and therefore at a distance from the passengers and the electronic systems of the aircraft.Type: GrantFiled: September 15, 2020Date of Patent: May 30, 2023Assignee: AIRBUS OPERATIONS SASInventors: Olivier Ciet, Pascal Pome, Alistair Forbes
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Patent number: 11572191Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.Type: GrantFiled: July 15, 2022Date of Patent: February 7, 2023Assignees: AIRBUS OPERATIONS SAS, AIRBUS SAS, AIRBUS OPERATIONS S.L.Inventors: Jean-François Allias, Franck Alvarez, Pascal Pome, Nicolas Jolivet, Rémi Amargier, Salvatore Demelas, Norberto Simionato Neto, Benedikt Bammer, Damien Mariotto
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Publication number: 20230021085Abstract: A propeller-type propulsion system for aircraft, comprises a propeller, a plurality of electric motors comprising nested coaxial respective driveshafts, and a gearbox having an output shaft onto which the propeller is mechanically coupled, and an input shaft to which the coaxial driveshafts of the electric motors are mechanically coupled. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.Type: ApplicationFiled: July 15, 2022Publication date: January 19, 2023Inventors: Jean-François ALLIAS, Franck ALVAREZ, Pascal POME, Nicolas JOLIVET, Rémi AMARGIER, Salvatore DEMELAS, Norberto SIMIONATO NETO, Benedikt BAMMER, Damien MARIOTTO
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Publication number: 20230017954Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.Type: ApplicationFiled: July 15, 2022Publication date: January 19, 2023Inventors: Jean-François ALLIAS, Franck ALVAREZ, Pascal POME, Nicolas JOLIVET, Rémi AMARGIER, Salvatore DEMELAS, Norberto SIMIONATO NETO, Benedikt BAMMER, Damien MARIOTTO
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Publication number: 20220411084Abstract: A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.Type: ApplicationFiled: June 27, 2022Publication date: December 29, 2022Inventors: Pascal POME, Nicolas JOLIVET, Rémi AMARGIER, Lionel CZAPLA, Franck ALVAREZ, Kotaro FUKASAKU, Benoît PENVEN, Delphine JALBERT, Laurent LAFONT, Milan TASIC, Frédéric GOUPIL, Jean-Victor LAPEYRE, Emmanuel MERMOZ
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Publication number: 20220355942Abstract: A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.Type: ApplicationFiled: May 2, 2022Publication date: November 10, 2022Inventors: Pascal POME, Lionel CZAPLA, Benjamin THUBERT
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Publication number: 20220306306Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.Type: ApplicationFiled: March 23, 2022Publication date: September 29, 2022Inventors: Christophe LABARTHE, Franck ALVAREZ, Fabien LATOURELLE, Olivier VERSEUX, Pascal POME, Jean Francois ALLIAS, Olivier CIET, Olivier RASPATI, Anthony ROUX, Benedikt BAMMER
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Patent number: 11254437Abstract: An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.Type: GrantFiled: October 3, 2018Date of Patent: February 22, 2022Assignee: AIRBUS OPERATIONS SASInventors: Frederic Journade, Eric Bouchet, Olivier Barbara, Pascal Pome
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Publication number: 20210078702Abstract: An aircraft having a fuselage having a pressurized upper space above the floor and a lower space beneath the floor, a wing, a hollow support stay fixed between the lower space level of the fuselage and the wing, an electric motor propeller propulsion system fixed beneath each wing, the output shaft of the motor driving a propeller in rotation, a production system having a fuel cell producing electrical energy supplying the electric motor with electricity via electrical conductors, a hydrogen reservoir fixed in the lower space, and a hydrogen inlet pipe feeding hydrogen from a hydrogen reservoir to the production system, wherein the hydrogen inlet pipe extends through the interior of the support stay. The electrical conductors or the hydrogen pipes pass through the stays on the outside of the fuselage and therefore at a distance from the passengers and the electronic systems of the aircraft.Type: ApplicationFiled: September 15, 2020Publication date: March 18, 2021Inventors: Olivier CIET, Pascal POME, Alistair FORBES
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Patent number: 10336458Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.Type: GrantFiled: December 18, 2014Date of Patent: July 2, 2019Assignee: AIRBUS OPERATIONS (S.A.S.)Inventors: Julien Guillemaut, Sébastien Alby, Jérôme Colmagro, Pascal Pome, Jonathan Blanc, Thomas Robiglio, Tobias Sjostrom
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Publication number: 20190100324Abstract: An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.Type: ApplicationFiled: October 3, 2018Publication date: April 4, 2019Inventors: Frederic JOURNADE, Eric BOUCHET, Olivier BARBARA, Pascal POME
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Publication number: 20150259074Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.Type: ApplicationFiled: December 18, 2014Publication date: September 17, 2015Inventors: Julien Guillemaut, Sébastien Alby, Jérôme Colmagro, Pascal Pome, Jonathan Blanc, Thomas Robiglio, Tobias Sjostrom