公开(公告)号：US20200017227A1

公开(公告)日：2020-01-16

申请号：US16437260

申请日：2019-06-11

Applicant: Airbus Operations SAS

Inventor： Thomas DEFORET ,  Benoit ORTEU ,  Olivier GLEIZE

IPC: B64D27/26 ,  B64D27/18

Abstract: A mounting pylon comprising a structure that comprises two C-shaped semi-structures and comprising an upper spar, a lower spar and a lateral flank, an upper panel, a lower panel, a reacting attachment point, two bars attached between the reacting attachment point and a jet engine, and a front wing attachment point attached to a wing box. The lateral flank comprises joists that are aligned between the front wing attachment point and the reacting attachment point, and where the angles between two successive joists are equal.

公开(公告)号：US20180178923A1

公开(公告)日：2018-06-28

申请号：US15849243

申请日：2017-12-20

Applicant: Airbus Operations SAS

Inventor： Isabelle PETRISSANS-LLOVERAS ,  Guillaume GALLANT ,  Olivier GLEIZE ,  Olivier DUBOIS ,  Aurelien PANTEL

IPC: B64D27/26 ,  B64D27/18 ,  B64F5/10

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/264 ,  B64F5/10 ,  Y02T50/44

Abstract: Fixation of an aircraft engine attachment pylon to the wing of an aircraft by means of an attachment device attached to a wing structure by means of first attachment through-members. The attachment device and the attachment pylon have respective junction surfaces clamped to each other by means of second attachment through-members. The junction surfaces extend along a plane forming an angle of less than 45 degrees with a vertical direction of the aircraft. A method for assembling the attachment pylon to the wing includes the positioning of the attachment pylon facing the attachment device, and then the clamping of the respective junction surfaces of the attachment device and of the attachment pylon to each other via the second attachment through-members.

公开(公告)号：US20200269987A1

公开(公告)日：2020-08-27

申请号：US16782271

申请日：2020-02-05

Applicant: Airbus Operations SAS

Inventor： Olivier GLEIZE

IPC: B64D27/26 ,  B64D29/02

Abstract: A primary structure of an aircraft pylon, which comprises upper and lower spars, right-hand and left-hand lateral panels, transverse reinforcers that are disposed in transverse planes and, each have a square or rectangular contour and at least one sole to which the upper and lower spars and the right-hand and left-hand lateral panels are fastened. At least one of the transverse reinforcers of the primary structure has first and second link rods that are oriented along diagonals of the transverse reinforcer, and connecting systems that each connect first and second ends of the first and second link rods to the sole or to one of the soles.

公开(公告)号：US20180305032A1

公开(公告)日：2018-10-25

申请号：US15956154

申请日：2018-04-18

Applicant: Airbus Operations SAS

Inventor： Guillaume GALLANT ,  Olivier GLEIZE

IPC: B64D27/26 ,  F02C7/20

CPC classification number: B64D27/26 ,  B64D27/12 ,  B64D27/18 ,  B64D2027/266 ,  F02C7/20

Abstract: An engine assembly for an aircraft, comprising an engine mounting pylon comprising a primary structure forming a box closed by a front closing rib, a front engine mount comprising at least two connecting link rods that are disposed laterally on either side of the box and each comprise a first end mounted on a first fitting of the casing. The rib forms a part of the front mount, comprising at least one transverse fitting made in one piece so as to close a front end of the box and to have lugs protruding laterally on each side of the box, each lug being provided with a first orifice for mounting a second end of one of the link rods.