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

IPC: B64D27/24 ,  B64D27/26

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.

公开(公告)号：US20210311522A1

公开(公告)日：2021-10-07

申请号：US17222153

申请日：2021-04-05

Applicant: Airbus Operations SAS

Inventor： Christophe VLACICH ,  Bertrand DESHAYES ,  Frédéric VIADER ,  Laurent LAFONT

IPC: G06F1/12 ,  G06F1/08 ,  G06F9/48 ,  B64D45/00

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.

公开(公告)号：US20170240288A1

公开(公告)日：2017-08-24

申请号：US15437698

申请日：2017-02-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Laurent LAFONT ,  Pascal Gougeon

IPC: B64D29/06 ,  B64D27/26

CPC classification number: B64D29/06 ,  B64D27/16 ,  B64D27/26 ,  B64D2027/262 ,  B64D2027/264

Abstract: In order to reduce the size of the attachment arrangement between an aircraft engine and its attachment device, an engine assembly is provided for which the primary structure of the attachment device includes a central box and two movable structural cowls. Further the arrangement for attaching the engine on the structure comprises a group of main ties laid out in a main transverse plane for absorbing forces crossing a front end of the movable structural cowls, this group comprising three main shearing pins radially oriented and distributed around a longitudinal axis of the engine, each pin crossing a first shearing orifice provided on a fitting secured to the hub of the intermediate case on the one hand, and a second shearing orifice provided on one of the movable cowls or on its connecting structure to the central box on the other hand.

公开(公告)号：US20240317418A1

公开(公告)日：2024-09-26

申请号：US18608132

申请日：2024-03-18

Applicant: Airbus Operations SAS

Inventor： Laurent LAFONT

IPC: B64D37/30 ,  B64D27/40 ,  B64D33/04 ,  B64D37/34 ,  F02K1/82

CPC classification number: B64D37/30 ,  B64D27/40 ,  B64D33/04 ,  B64D37/34 ,  F02K1/822

Abstract: A propulsion assembly comprising a propulsion system including at least one exhaust duct, from which an exhaust gas stream is discharged, and also a debris ejection zone, a supply device, configured to supply the propulsion system with gaseous fuel, including at least one conditioning system for the gaseous fuel, at least one enclosure in which the conditioning system is positioned, the enclosure being located in the propulsion assembly behind the debris ejection zone. Also an aircraft including at least one such propulsion assembly.

公开(公告)号：US20190233129A1

公开(公告)日：2019-08-01

申请号：US16264909

申请日：2019-02-01

Applicant: Airbus Operations SAS

Inventor： Laurent LAFONT ,  Stéphane DIDA ,  Jérôme COLMAGRO

IPC: B64D27/26 ,  B64C3/18

CPC classification number: B64D27/26 ,  B64C3/185 ,  B64C3/187 ,  B64D27/18 ,  B64D2027/264

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.