公开(公告)号：US20190100324A1

公开(公告)日：2019-04-04

申请号：US16150991

申请日：2018-10-03

申请人： AIRBUS OPERATIONS SAS

发明人： Frederic JOURNADE ,  Eric BOUCHET ,  Olivier BARBARA ,  Pascal POME

IPC分类号： B64D27/26 ,  B64D27/18

摘要： 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.

公开(公告)号：US20240025553A1

公开(公告)日：2024-01-25

申请号：US18355779

申请日：2023-07-20

申请人： Airbus Operations SAS

发明人： Mathieu MAHE ,  Christophe LABARTHE ,  Frederic JOURNADE ,  Frédéric VINCHES ,  Franck ALVAREZ ,  Lionel CZAPLA ,  Emmanuel VARDELLE ,  Rémi AMARGIER ,  Kotaro FUKASAKU

IPC分类号： B64D27/24 ,  H01M8/2465

CPC分类号： B64D27/24 ,  H01M8/2465 ,  B64D2027/264

摘要： A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

公开(公告)号：US20180009543A1

公开(公告)日：2018-01-11

申请号：US15641771

申请日：2017-07-05

申请人： Airbus Operations SAS

发明人： Frederic JOURNADE ,  Eric BOUCHET ,  Nicolas GROSSEAU ,  Antoine MUTIN

IPC分类号： B64D27/26

CPC分类号： B64D27/26 ,  B64D2027/266 ,  F16B37/047

摘要： An aircraft engine mount which comprises first and second parts connected by connecting elements and wherein one of the two connected parts comprises at least one transverse hole opening onto an access face of the part and into which there open at least two passage holes each intended to house a threaded shank of one of the connecting elements. The engine mount comprises a transverse nut which comprises at least two bodies joined together each having a tapped hole configured to engage with one of the threaded shanks.