公开(公告)号：US20190152616A1

公开(公告)日：2019-05-23

申请号：US16197726

申请日：2018-11-21

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Eric BOUCHET ,  Olivier BARBARA

IPC: B64D27/26

Abstract: To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

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

IPC: B64D27/26 ,  B64D27/18

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.