公开(公告)号：US09593708B2

公开(公告)日：2017-03-14

申请号：US14553432

申请日：2014-11-25

Applicant: Airbus Operations (SAS)

Inventor： Jerome Cassagne ,  Thomas Deforet

IPC: F16B39/24 ,  B64D27/26 ,  F16B39/10 ,  F16C11/04 ,  F16B39/04

CPC classification number: F16B39/24 ,  B64D27/26 ,  F16B39/04 ,  F16B39/108 ,  F16C11/04 ,  F16C11/045 ,  F16C11/0614 ,  F16C23/045 ,  F16C2326/43 ,  Y10T403/32893

Abstract: An assembly with an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis. The assembly comprises a blocking device. The blocking device comprises a nut screwed onto a threaded portion of an extension of the second sleeve and comprising an inner shoulder against which the second end of the articulation spindle can come to bear, a locking washer able to adopt a locked state in which it prevents the nut from rotating with respect to the extension and an unlocked state in which it allows the nut to be unscrewed, and a longilinear element able to adopt a locked state in which it passes through at least the nut so as to prevent it from rotating.

Abstract translation: 一种具有安装在插入到U形夹的第一臂中的第一套筒中并且插入到所述U形夹的第二臂中的第二套筒中的铰接轴的组件。 组件包括阻挡装置。 阻塞装置包括拧在第二套筒的延伸部分的螺纹部分上的螺母，并包括一个内肩，使得铰接主轴的第二端可以承受的内肩，能够采用锁定状态的锁紧垫圈， 螺母相对于延伸部旋转，并且其中允许螺母被拧开的解锁状态，以及能够采用锁定状态的长线形元件，其中至少穿过螺母以防止其旋转。

公开(公告)号：US20150166190A1

公开(公告)日：2015-06-18

申请号：US14553416

申请日：2014-11-25

Applicant: Airbus Operations (SAS)

Inventor： Jerome Cassagne ,  Thomas Deforet

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/262 ,  F16B39/04 ,  F16B39/10 ,  Y10T403/32041

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis said assembly comprising a blocking device. The blocking device comprising a screw with a first cylindrical portion which is screwed into an extension of the second sleeve and against which the second end of the articulation spindle can come to press, and a second portion, in the extension of the first portion, with a smaller cross section than said first cylindrical portion, a locking washer which is interposed between the second portion of the screw and the extension of the second sleeve in a locked position, and a longilinear element which passes through the screw and the second sleeve in a locked state.

Abstract translation: 一种组件，其具有安装在插入到U形夹的第一臂中的第一套筒中的铰接轴和插入到所述U形夹的第二臂中的第二套筒，所述组件包括阻挡装置。 所述阻塞装置包括螺钉，所述螺钉具有第一圆柱形部分，所述第一圆柱形部分旋入所述第二套筒的延伸部分中，并且所述关节运动主轴的第二端可以抵靠所述第一圆柱形部分，所述第一部分的所述延伸部中的第二部分与 比所述第一圆柱形部分更小的横截面;锁定垫圈，其被插入在所述螺钉的第二部分和所述第二套筒在锁定位置的延伸部之间;以及线性元件，其穿过所述螺钉和所述第二套筒， 锁定状态。

公开(公告)号：US11542025B2

公开(公告)日：2023-01-03

申请号：US17407251

申请日：2021-08-20

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Thomas Deforet ,  Jacky Puech

IPC: B64D27/26

Abstract: A propulsion assembly including a primary structure of a pylon having right and left extensions projecting with respect to right and left lateral panels of the primary structure and also right and left brackets, each having a first flank connected to the right or left lateral panel of the primary structure and a second flank pressed against the right or left extension, a front engine mount having first and second links, each connected to an engine and directly to the front transverse reinforcement by a first or second reinforcement connection pin passing through the right or left extension and the second flank of the right or left bracket.

公开(公告)号：US11345479B2

公开(公告)日：2022-05-31

申请号：US16363513

申请日：2019-03-25

Applicant: Airbus Operations SAS

Inventor： Jean Geliot ,  Thomas Deforet ,  Adeline Soulie ,  Olivier Dubois

IPC: B64D27/26

Abstract: An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.

公开(公告)号：US11325715B2

公开(公告)日：2022-05-10

申请号：US16807351

申请日：2020-03-03

Applicant: Airbus Operations SAS

Inventor： Thomas Deforet ,  Rémi Lansiaux ,  Olivier Dubois ,  Anthony Mertes ,  David Alric ,  Stéphane Nogues

IPC: B64D27/26

Abstract: A linking device connecting an aircraft engine and a primary structure of an aircraft pylon, comprising a support connected to the primary structure, a spreader, extending between first and second ends that has a central part connected to the support by a principal link comprising a principal rotation axis, at least one system for limiting the deflection of the spreader comprising an extension secured to the spreader and also upper and lower stops, secured to a fitting secured to the support, between which the extension is positioned.

公开(公告)号：US09828103B2

公开(公告)日：2017-11-28

申请号：US14553416

申请日：2014-11-25

Applicant: Airbus Operations (SAS)

Inventor： Jerome Cassagne ,  Thomas Deforet

IPC: B64D27/26 ,  F16B39/10 ,  F16B39/04

CPC classification number: B64D27/26 ,  B64D2027/262 ,  F16B39/04 ,  F16B39/10 ,  Y10T403/32041

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis said assembly comprising a blocking device. The blocking device comprising a screw with a first cylindrical portion which is screwed into an extension of the second sleeve and against which the second end of the articulation spindle can come to press, and a second portion, in the extension of the first portion, with a smaller cross section than said first cylindrical portion, a locking washer which is interposed between the second portion of the screw and the extension of the second sleeve in a locked position, and a longilinear element which passes through the screw and the second sleeve in a locked state.

公开(公告)号：US09573694B2

公开(公告)日：2017-02-21

申请号：US14719583

申请日：2015-05-22

Applicant: Airbus Operations (SAS)

Inventor： Jerome Cassagne ,  Antoine Cousin ,  Thomas Deforet

IPC: B64D27/26 ,  F16C23/04

CPC classification number: B64D27/26 ,  B64D2027/262 ,  F16C23/046 ,  F16C2326/43

Abstract: An engine fastener for an aircraft, to secure an engine to a pylon and comprising a fastener body fixed to the pylon and having a cylindrical extension, and a fixing assembly comprising a paddle fixed to the engine and a connection arrangement joined to the paddle and arranged on the cylindrical extension to form a ball-and-socket joint between the cylindrical extension and the paddle. The connection arrangement comprises a ball, formed in one piece, having a central bore in which the cylindrical extension fits, and of which the outer surface is a spherical portion, a fixing element fixing the ball on the cylindrical extension, and two cages, each having an inner surface assuming the form of a spherical portion. The two inner surfaces are arranged opposite one another to house the ball, and for each cage, a joining element joins the cage to the paddle.

Abstract translation: 一种用于飞行器的发动机紧固件，用于将发动机固定到挂架上并且包括固定到塔架上并具有圆柱形延伸部的紧固件主体，以及固定组件，其包括固定到发动机的桨叶和连接到桨叶的连接装置， 在圆柱形延伸部上形成圆柱形延伸部和桨板之间的球窝接头。 连接装置包括一个成形为一体的球，具有中心孔，圆柱形延伸部配合在其中，外表面是球形部分，将球固定在圆柱形延伸部上的固定元件，以及两个笼子 具有呈现球形部分形式的内表面。 两个内表面彼此相对布置以容纳球，并且对于每个笼，连接元件将笼连接到桨。

公开(公告)号：US09399520B2

公开(公告)日：2016-07-26

申请号：US14563040

申请日：2014-12-08

Applicant: Airbus Operations (SAS)

Inventor： Jerome Cassagne ,  Thomas Deforet

IPC: B64D27/26 ,  F16B39/10 ,  F16C11/04 ,  F16C23/04

CPC classification number: B64D27/26 ,  B64D2027/262 ,  F16B39/10 ,  F16C11/045 ,  F16C23/045 ,  F16C2326/43 ,  Y10T403/32557

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis, and a blocking device. The blocking device comprises a nut screwed onto an extension of the second sleeve and comprising an inner shoulder acting as a stop for a second end of the articulation spindle, at least two locking washers engaging with the nut, a tab washer comprising an element immobilizing it in rotation with respect to the second arm of the clevis, and for each locking washer, a blocking element limiting the rotational movement of the locking washer with respect to the tab washer.

Abstract translation: 一种组件，其具有安装在插入到U形夹的第一臂中的第一套筒和插入到所述U形夹的第二臂中的第二套筒中的铰接轴以及阻挡装置。 所述阻塞装置包括拧在所述第二套筒的延伸部上的螺母，并且包括作为所述铰接轴的第二端的止动件的内肩，与所述螺母啮合的至少两个锁定垫圈，包括固定其的元件 相对于U形夹的第二臂旋转，并且对于每个锁定垫圈，阻挡元件限制锁定垫圈相对于凸耳垫圈的旋转运动。

公开(公告)号：US20150166191A1

公开(公告)日：2015-06-18

申请号：US14563040

申请日：2014-12-08

Applicant: Airbus Operations (SAS)

Inventor： Jerome Cassagne ,  Thomas Deforet

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/262 ,  F16B39/10 ,  F16C11/045 ,  F16C23/045 ,  F16C2326/43 ,  Y10T403/32557

Abstract: An assembly having an articulation spindle mounted in a first sleeve inserted into a first arm of a clevis and in a second sleeve inserted into a second arm of said clevis, and a blocking device. The blocking device comprises a nut screwed onto an extension of the second sleeve and comprising an inner shoulder acting as a stop for a second end of the articulation spindle, at least two locking washers engaging with the nut, a tab washer comprising an element immobilizing it in rotation with respect to the second arm of the clevis, and for each locking washer, a blocking element limiting the rotational movement of the locking washer with respect to the tab washer.

Abstract translation: 一种组件，其具有安装在插入到U形夹的第一臂中的第一套筒和插入到所述U形夹的第二臂中的第二套筒中的铰接轴以及阻挡装置。 所述阻塞装置包括拧在所述第二套筒的延伸部上的螺母，并且包括作为所述铰接轴的第二端的止动件的内肩，与所述螺母啮合的至少两个锁定垫圈，包括固定其的元件 相对于U形夹的第二臂旋转，并且对于每个锁定垫圈，阻挡元件限制锁定垫圈相对于凸耳垫圈的旋转运动。

公开(公告)号：US12054271B2

公开(公告)日：2024-08-06

申请号：US17391825

申请日：2021-08-02

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Sebastien Alby ,  Jean Geliot ,  Thomas Deforet ,  Olivier Dubois ,  Joël Dedieu ,  Xavier Bardey

IPC: B64D27/40 ,  B64F5/10

CPC classification number: B64D27/40 ,  B64F5/10

Abstract: A method for assembling an aircraft pylon including a primary structure and at least one internal system positioned at least partially within the primary structure, wherein the assembly method includes a first step of assembling a part of the primary structure so that the interior of the primary structure remains accessible, a step of mounting an internal systems module including at least one support and at least one internal system connected to the support, a second step of assembling the internal systems module and the partially assembled primary structure, a third step of assembling any element of the primary structure not assembled in the first assembly step, and an aircraft pylon assembled by such a method.