公开(公告)号：US20230030853A1

公开(公告)日：2023-02-02

申请号：US17868161

申请日：2022-07-19

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA ,  Olivier PAUTIS

IPC: B64D27/18

Abstract: A propulsion assembly having a jet engine with a central casing, an attachment pylon having a rigid structure, a front engine attachment and a device for reacting the thrust forces. The front engine attachment has, on either side of a median plane, a front rod articulated via a connection point respectively to the rigid structure and to the central casing, and the reaction device has two central rods, two first fittings as one with the rigid structure and two second fittings as one with the central casing, wherein the two first fittings are independent of one another and wherein each central rod is articulated between a first fitting and a second fitting.

公开(公告)号：US20240199218A1

公开(公告)日：2024-06-20

申请号：US18541513

申请日：2023-12-15

Applicant: Airbus Operations SAS

Inventor： Olivier PAUTIS ,  Paolo MESSINA ,  Jonathan BLANC ,  Thomas ROBIGLIO ,  Thomas FIRMIGNAC

IPC: B64D29/06 ,  B64D29/02

CPC classification number: B64D29/06 ,  B64D29/02

Abstract: An aircraft having a fixed structure, an engine pylon, and a cowling system, a slider bearing a rear cowl and able to move in translation from an advanced position to a retracted position, a displacement system having, on either side of a median plane of the engine pylon, a guide as one with the fixed structure, a sliding element as one with the slider and sliding along each guide disposed on the same side, and a support as one with the fixed structure and having a blade parallel to the translation direction and on which a surface parallel to the translation direction of the slider rests. The presence of the mobile cowl ensures, inter alia, easy access to the inside of the engine pylon and to the systems that are housed therein.

公开(公告)号：US20250074608A1

公开(公告)日：2025-03-06

申请号：US18457148

申请日：2023-08-28

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA ,  Thomas ROBIGLIO ,  Thomas FIRMIGNAC

IPC: B64D27/26 ,  B64F5/10

Abstract: An aircraft pylon comprising an aircraft pylon fairing extending along a longitudinal axis, a primary structure having a peg that is inserted in a through opening of an inner rib of the fairing and four yokes as well as four removable fixing elements that can be inserted from the outside of the fairing. The fixing elements are inserted in a direction perpendicular to said longitudinal axis of the fairing in order to hold in place a fitting of the primary structure that has an oblong through opening and is inserted into one of said yokes of the fairing. Also a method of assembling an aircraft pylon and an aircraft with such a pylon.

公开(公告)号：US20190308739A1

公开(公告)日：2019-10-10

申请号：US16367585

申请日：2019-03-28

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA

IPC: B64D29/06 ,  F16C11/10

Abstract: A pivoting-connection device connecting at least two components and comprising a clevis having first and second branches, an arm positioned between the first and second branches of the clevis, a cylindrical pin connecting the clevis and the arm, at least one guide ring which has a flange configured to bear against an interior face of the first branch, an immobilizing system configured to occupy a free state and a blocked state in which the cylindrical pin and the guide ring are immobilized with respect to one another in the longitudinal direction, in both senses of that direction, and a blocking system configured to occupy an unfitted state and a blocked state in which the blocking system is in contact with the exterior face of the first branch.

公开(公告)号：US20230202665A1

公开(公告)日：2023-06-29

申请号：US18073049

申请日：2022-12-01

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA ,  Olivier PAUTIS

IPC: B64D29/06 ,  B64D27/26

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

Abstract: An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

公开(公告)号：US20230122444A1

公开(公告)日：2023-04-20

申请号：US17964083

申请日：2022-10-12

Applicant: Airbus Operations SAS

Inventor： Franck RUMIEL ,  Thomas ROBIGLIO ,  Paolo MESSINA

IPC: B64D27/26

Abstract: An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

公开(公告)号：US20200232500A1

公开(公告)日：2020-07-23

申请号：US16745643

申请日：2020-01-17

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA

IPC: F16B39/06 ,  F16B37/04

Abstract: A bolt comprising a threaded shaft having at least one helical thread and at least one longitudinal groove, a nut having a tapped hole configured to be screwed onto the threaded shaft, and at least one diagonal slot which includes a first opening end and a second non-opening end. The diagonal slot is inclined from the first end towards the second end in the same direction as the helical thread of the threaded shaft. An anti-rotation device is configured to rotationally immobilize the nut with respect to the threaded shaft and comprises a ring which surrounds at least the threaded shaft and which has at least one first toe configured to be housed in the longitudinal groove of the threaded shaft and in the diagonal slot of the nut, in operation.

公开(公告)号：US20220204155A1

公开(公告)日：2022-06-30

申请号：US17502417

申请日：2021-10-15

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA ,  Olivier PAUTIS

IPC: B64C3/32 ,  B64F5/10

Abstract: An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

公开(公告)号：US20210269167A1

公开(公告)日：2021-09-02

申请号：US17114703

申请日：2020-12-08

Applicant: Airbus Operations SAS

Inventor： Jérôme COLMAGRO ,  Paolo MESSINA

IPC: B64D27/26 ,  B64F5/10 ,  F16C11/04

Abstract: An assembly including a link axis supported by first and second guiding rings positioned in first and second branches of a clevis, one of the guiding rings including a tubular extension, protruding with respect to an outer face of one of the branches, which has a threaded portion on its outer circumferential face. Complementing this, the assembly includes a nut configured to be screwed onto the threaded portion of the tubular extension and an immobilization system configured to immobilize the nut in translation and/or in rotation, the nut and the link axis being linked by a complete link that is non-removable or that forms a single-piece part. This solution makes it possible to reduce the number of parts forming the assembly. Also provided are an engine attachment and an aircraft including such an assembly.

公开(公告)号：US20200262040A1

公开(公告)日：2020-08-20

申请号：US16778202

申请日：2020-01-31

Applicant: Airbus Operations SAS

Inventor： Paolo MESSINA

IPC: B25B29/00 ,  F16B39/32

Abstract: An unlocking tool configured for unlocking a locking system that prevents a nut from rotating with respect to a threaded stem, comprising a ring configured to be positioned around the threaded stem in operation and at least one finger extending between a first end connected to the ring and a second, free end, this finger being configured to be received and slide in a longitudinal channel of the threaded stem in operation, each finger comprising a front face that is configured to cooperate with at least one tab of the locking system so as to prevent it becoming immobilized in one of the longitudinal channels of the threaded stem.