公开(公告)号：US11981446B2

公开(公告)日：2024-05-14

申请号：US17878360

申请日：2022-08-01

Applicant: Airbus Operations SAS

Inventor： Umberto Gastaldi ,  Wolfgang Brochard ,  Olivier Pautis

IPC: B64D29/08 ,  B64D29/06

CPC classification number: B64D29/08 ,  B64D29/06

Abstract: An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

公开(公告)号：US10829233B2

公开(公告)日：2020-11-10

申请号：US15850115

申请日：2017-12-21

Applicant: Airbus Operations SAS

Inventor： Wolfgang Brochard

IPC: B64D27/26 ,  F02C7/20

Abstract: For fitting of a front engine attachment of an engine assembly for an aircraft, a shearing pin is oriented in a longitudinal direction and is integral with a front closure rib of the strut housing and projects forward, a main attachment body is arranged axially opposite the intermediate casing hub, at the rear of the latter, the main attachment body having an orifice for accommodation of the shearing pin, an arrangement for securing the main attachment body on the engine, and an arrangement for axial retention of the main attachment body relative to the rib, the axial retention arrangement comprising first screws, the heads of which cooperate with the rib, as well as barrel nuts which cooperate with the screws, and are accommodated in the main attachment body.

公开(公告)号：US09180975B2

公开(公告)日：2015-11-10

申请号：US14140515

申请日：2013-12-25

Applicant: Airbus Operations (SAS)

Inventor： Wolfgang Brochard ,  Romain Terral

IPC: B64D27/26 ,  F16F1/50

CPC classification number: B64D27/26 ,  F16F1/50

Abstract: A linking device including two hinge pins and having flexibility allowing vibrations between these two shafts to be filtered. The device includes a stack of plates connected to one another by layers of elastomer material. Plates of a first type are coupled to one of the shafts in relation to the movements parallel to the plates, while the plates of a second type are coupled to the other shaft in relation to the movements parallel to the plates, so as to allow relative movement of the shafts parallel to the plates. This linking device may be used in particular as a connecting rod, spreader beam or three-point shackle used in connecting a turbine engine to a pylon in a propulsion system of an aircraft such as an airplane.

Abstract translation: 连接装置包括两个铰链销并且具有允许这两个轴之间的振动被过滤的灵活性。 该装置包括通过弹性体材料层彼此连接的一叠板。 第一类型的板相对于平行于板的运动耦合到一个轴，而第二类的板相对于平行于板的运动而耦合到另一个轴，以便允许相对 轴的平行于板的运动。 该连接装置可特别用作将涡轮发动机连接到诸如飞机的飞行器的推进系统中的塔架的连杆，吊架梁或三点卸扣。

公开(公告)号：US09975641B2

公开(公告)日：2018-05-22

申请号：US14707240

申请日：2015-05-08

Applicant: Airbus Operations (SAS)

Inventor： Wolfgang Brochard ,  Misael Hernandez-Perez ,  Yves Belloc

IPC: B64D27/26 ,  F28F3/02

CPC classification number: B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F28F3/02

Abstract: Housing a conduit of a thermal protection system of a rigid structure of an attachment pylon in an aircraft propulsion assembly within a box of the rigid structure, so as to take advantage of the volume within the rigid structure. The elements forming the conduits thus form an integral part of the rigid structure and can thus play a structural role.

公开(公告)号：US09328630B2

公开(公告)日：2016-05-03

申请号：US14016296

申请日：2013-09-03

Applicant: Airbus Operations (SAS)

Inventor： Wolfgang Brochard ,  Romain Terral

IPC: B64D27/00 ,  F01D25/24 ,  B64D27/20 ,  B64D27/26 ,  B64D29/06

CPC classification number: F01D25/24 ,  B64D27/20 ,  B64D27/26 ,  B64D29/06 ,  Y02T50/44

Abstract: A propulsion unit for an aircraft, comprising one turbine engine and a mounting device for a turbine engine designed to be added laterally on an aircraft structure and comprising a rigid mounting structure. The rigid mounting structure supports at least one arch which is concave towards the longitudinal axis of the propulsion unit and which has a distal end at an angular distance of between 45 and 120 degrees from a vertical plane passing through the axis, on the other side of the structure, and supporting a distal connecting element connecting the turbine engine to the arch.

Abstract translation: 一种用于飞机的推进单元，包括一个涡轮发动机和用于涡轮发动机的安装装置，该涡轮发动机设计成横向地添加在飞行器结构上并且包括刚性安装结构。 刚性安装结构支撑至少一个拱形件，该拱形件朝向推进单元的纵向轴线是凹形的，并且具有与通过轴线的垂直平面成45度到120度之间的角距离的远端，在另一侧 并且支撑将涡轮发动机连接到拱顶的远端连接元件。

公开(公告)号：US20140183297A1

公开(公告)日：2014-07-03

申请号：US14140512

申请日：2013-12-25

Applicant: Airbus Operations (SAS)

Inventor： Wolfgang Brochard ,  Romain Terral

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D27/00 ,  B64D2027/266

Abstract: A boomerang link for aircraft engine mounts, including a first orifice and a second orifice both designed to connect the boomerang link to an aircraft pylon, and a third orifice designed to connect the boomerang link to an aircraft engine. The third orifice is offset relative to a plane passing simultaneously through an axis of the first orifice and through an axis of the second orifice. When the boomerang link is seen in section in any plane orthogonal to the axes, a straight line segment extending from the axis of the second orifice to an axis of the third orifice crosses a region external to the boomerang link. This conformation confers on the boomerang link a flexibility enabling it to filter transverse vibrations between an engine and an aircraft pylon.

Abstract translation: 用于飞行器发动机支架的回旋式离合器连接件，包括设计成将回旋臂连杆连接到飞机塔架的第一孔口和第二孔口以及用于将飞旋镖杆连接到飞机发动机的第三孔。 第三孔相对于同时穿过第一孔的轴线并穿过第二孔的轴线的平面偏移。 当在与轴正交的任何平面中的截面中看到飞旋镖连杆时，从第二孔的轴线延伸到第三孔的轴线的直线段穿过回旋形连杆的外部区域。 这种构想赋予了回旋镖连杆的灵活性，使其能够过滤发动机和飞机塔架之间的横向振动。

公开(公告)号：US12053915B2

公开(公告)日：2024-08-06

申请号：US17953553

申请日：2022-09-27

Applicant: Airbus Operations SAS

Inventor： Wolfgang Brochard ,  Laurent Cazeaux ,  Florian Ravise

IPC: B29C45/14 ,  B29C45/00 ,  B29C51/00 ,  F02K1/62 ,  B29K105/16 ,  B29K671/00 ,  B29L31/30

CPC classification number: B29C45/14786 ,  B29C45/0013 ,  B29C45/0053 ,  B29C45/14 ,  B29C45/14065 ,  B29C45/1418 ,  B29C51/004 ,  F02K1/62 ,  B29C2045/14442 ,  B29K2105/16 ,  B29K2671/00 ,  B29L2031/3076

Abstract: A door for a thrust reversal system, an aircraft with such a door, and a method for manufacturing a door of a thrust reversal system. The door comprises a wall formed from long fibers embedded in a thermoplastic resin matrix and a network of ribs overmolded on one of the faces of the wall. A propulsion assembly of an aircraft comprises a thrust reversal system having a plurality of such doors.

公开(公告)号：US10730602B2

公开(公告)日：2020-08-04

申请号：US15182672

申请日：2016-06-15

Applicant: Airbus Operations S.L. ,  Airbus Operations SAS

Inventor： Javier Toral Vazquez ,  Esteban Martino Gonzalez ,  Diego Folch Cortes ,  Pablo Goya Abaurrea ,  Vasilis Votsios ,  Michel Fouinnetau ,  Sylvain Roumegas ,  Wolfgang Brochard

IPC: B64D37/04 ,  B64D27/10 ,  B64D27/14 ,  B64C1/06 ,  B64D45/00 ,  B64C1/00

Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.

公开(公告)号：US20150321765A1

公开(公告)日：2015-11-12

申请号：US14707240

申请日：2015-05-08

Applicant: Airbus Operations (SAS)

Inventor： Wolfgang Brochard ,  Misael Hernandez-Perez ,  Yves Belloc

IPC: B64D27/26 ,  F28F3/02

CPC classification number: B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F28F3/02

Abstract: Housing a conduit of a thermal protection system of a rigid structure of an attachment pylon in an aircraft propulsion assembly within a box of the rigid structure, so as to take advantage of the volume within the rigid structure. The elements forming the conduits thus form an integral part of the rigid structure and can thus play a structural role.

Abstract translation: 在刚性结构的箱体内的飞机推进组件中安装附接塔的刚性结构的热保护系统的导管，以便利用刚性结构内的体积。 因此，形成导管的元件形成刚性结构的组成部分，因此可以发挥结构作用。

公开(公告)号：US20140183298A1

公开(公告)日：2014-07-03

申请号：US14140515

申请日：2013-12-25

Applicant: Airbus Operations (SAS)

Inventor： Wolfgang Brochard ,  Romain Terral

IPC: B64D27/26

CPC classification number: B64D27/26 ,  F16F1/50

Abstract: A linking device including two hinge pins and having flexibility allowing vibrations between these two shafts to be filtered. The device includes a stack of plates connected to one another by layers of elastomer material. Plates of a first type are coupled to one of the shafts in relation to the movements parallel to the plates, while the plates of a second type are coupled to the other shaft in relation to the movements parallel to the plates, so as to allow relative movement of the shafts parallel to the plates. This linking device may be used in particular as a connecting rod, spreader beam or three-point shackle used in connecting a turbine engine to a pylon in a propulsion system of an aircraft such as an airplane.

Abstract translation: 连接装置包括两个铰链销并且具有允许这两个轴之间的振动被过滤的灵活性。 该装置包括通过弹性体材料层彼此连接的一叠板。 第一类型的板相对于平行于板的运动耦合到一个轴，而第二类的板相对于平行于板的运动而耦合到另一轴，以便允许相对 轴的平行于板的运动。 该连接装置可特别用作将涡轮发动机连接到诸如飞机的飞行器的推进系统中的塔架的连杆，吊架梁或三点卸扣。