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公开(公告)号：US20230021085A1
公开(公告)日：2023-01-19
申请号：US17865612
申请日：2022-07-15
Applicant: Airbus Operations SAS , Airbus SAS , Airbus Operations S.L.
Inventor： Jean-François ALLIAS , Franck ALVAREZ , Pascal POME , Nicolas JOLIVET , Rémi AMARGIER , Salvatore DEMELAS , Norberto SIMIONATO NETO , Benedikt BAMMER , Damien MARIOTTO
Abstract: 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.
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公开(公告)号：US20230017954A1
公开(公告)日：2023-01-19
申请号：US17866050
申请日：2022-07-15
Applicant: Airbus Operations SAS , Airbus SAS , Airbus Operations S.L.
Inventor： Jean-François ALLIAS , Franck ALVAREZ , Pascal POME , Nicolas JOLIVET , Rémi AMARGIER , Salvatore DEMELAS , Norberto SIMIONATO NETO , Benedikt BAMMER , Damien MARIOTTO
Abstract: 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.
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公开(公告)号：US20220411084A1
公开(公告)日：2022-12-29
申请号：US17849895
申请日：2022-06-27
Applicant: Airbus Operations SAS , Airbus SAS
Inventor： 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
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20220306306A1
公开(公告)日：2022-09-29
申请号：US17701818
申请日：2022-03-23
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Christophe LABARTHE , Franck ALVAREZ , Fabien LATOURELLE , Olivier VERSEUX , Pascal POME , Jean Francois ALLIAS , Olivier CIET , Olivier RASPATI , Anthony ROUX , Benedikt BAMMER
Abstract: 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.
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公开(公告)号：US20210078702A1
公开(公告)日：2021-03-18
申请号：US17021569
申请日：2020-09-15
Applicant: Airbus Operations SAS
Inventor： Olivier CIET , Pascal POME , Alistair FORBES
Abstract: 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.
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公开(公告)号：US20190100324A1
公开(公告)日：2019-04-04
申请号：US16150991
申请日：2018-10-03
Applicant: AIRBUS OPERATIONS SAS
Inventor： Frederic JOURNADE , Eric BOUCHET , Olivier BARBARA , Pascal POME
Abstract: 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.
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公开(公告)号：US20230415906A1
公开(公告)日：2023-12-28
申请号：US18339032
申请日：2023-06-21
Applicant: Airbus Operations SAS
Inventor： Kotaro FUKASAKU , Rémi AMARGIER , Lionel CZAPLA , Nicolas JOLIVET , Pascal POME
CPC classification number: B64D27/26 , B64D27/24 , H02K5/24 , B64D2027/262
Abstract: 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.
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公开(公告)号：US20220355942A1
公开(公告)日：2022-11-10
申请号：US17734212
申请日：2022-05-02
Applicant: Airbus Operations SAS
Inventor： Pascal POME , Lionel CZAPLA , Benjamin THUBERT
IPC: B64D27/24
Abstract: 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.
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