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公开(公告)号：US11565822B2
公开(公告)日：2023-01-31
申请号：US16708760
申请日：2019-12-10
Applicant: Airbus Operations SAS
Inventor： Philippe Auge , Benoit Orteu , Julien Bernat , Jean Geliot , Delphine Jalbert , Frédéric Ridray , Laurent Lafont , Pascal Gardes
Abstract: A propulsion assembly having a pylon, a turbomachine comprising an engine and a fan that is enclosed by a fan casing, a nacelle surrounding the engine and the fan casing and having a load support disposed in the top part of the nacelle, a front engine attachment between the pylon and a front part of the engine, a rear engine attachment between the pylon and a rear part of the engine, a front fan attachment between the fan casing and the load support, and a rear pylon attachment between the pylon and the load support. Such a propulsion assembly allows a reduction in bulk since the load of the turbojet engine is distributed between the load support and the pylon, and the pylon is attached to the engine.
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Patent Agency Ranking
公开(公告)号：US20210130001A1
公开(公告)日：2021-05-06
申请号：US17081193
申请日：2020-10-27
Applicant: Airbus Operations SAS
Inventor： Julien Allain , Stéphane Dida , Jérome Colmagro , Olivier Dubois , Julien Moulis , Jacky Puech , Laurent Lafont
Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.
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公开(公告)号：US11807373B2
公开(公告)日：2023-11-07
申请号：US17081193
申请日：2020-10-27
Applicant: Airbus Operations SAS
Inventor： Julien Allain , Stéphane Dida , Jérome Colmagro , Olivier Dubois , Julien Moulis , Jacky Puech , Laurent Lafont
CPC classification number: B64D27/26 , B64F5/10 , F16B5/08 , B64D2027/266
Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.
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公开(公告)号：US12291340B2
公开(公告)日：2025-05-06
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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公开(公告)号：US11027852B2
公开(公告)日：2021-06-08
申请号：US16264909
申请日：2019-02-01
Applicant: Airbus Operations SAS
Inventor： Laurent Lafont , Stéphane Dida , Jérôme Colmagro
Abstract: An assembly for an aircraft and comprising a wing comprising an airfoil box partly produced using a front spar, a mounting pylon arranged under the wing and comprising a primary structure formed as a primary box having a top spar extending at least partly under the airfoil box and having a slit, a bottom spar, lateral panels and a transverse reinforcing fixing rib, of which a bottom part is housed and fixed inside the primary structure and of which a top part passes through the slit. A fixing arrangement fixes the top part to the front spar. The fixing arrangement comprises a plurality of fixing bolts, where each fixing bolt fixes the top part to the front spar and has its axis at right angles to the fixing rib. Such an assembly allows the mounting pylon primary structure to be as close as possible to the wing.
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6.发明授权公开(公告)号：US11599141B2
公开(公告)日：2023-03-07
申请号：US17222153
申请日：2021-04-05
Applicant: Airbus Operations SAS
Inventor： Christophe Vlacich , Bertrand Deshayes , Frédéric Viader , Laurent Lafont
Abstract: A synchronizing system including a generation unit for generating a synchronizing pulse from data of an independent clock, the synchronizing pulse being generated in a periodic manner, transmission links to transmit the synchronizing pulse to all the computation units, and in each of the computation units, a control element to compare the synchronizing pulse that has been received to a pulse generated by an internal clock of the computation unit and to detect a compliance or a lack of compliance, a scheduler of each of the computation units activating a sequence of partitions when the synchronizing pulse is received, and this only if the control element has detected a compliance. The synchronizing system is configured to synchronize the computation units in a reliable and accurate manner and to increase the operating safety of these computation units.
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