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    AIRCRAFT ENGINE PYLON HAVING A MOVABLE ASSEMBLY OF COWLS
    1.
    发明申请
    AIRCRAFT ENGINE PYLON HAVING A MOVABLE ASSEMBLY OF COWLS 有权

    公开(公告)号：US20220315232A1

    公开(公告)日：2022-10-06

    申请号：US17708220

    申请日：2022-03-30

    申请人： Airbus Operations (S.A.S.)

    发明人： Olivier Pautis ,  Paolo Messina

    IPC分类号： B64D29/02 ,  B64D29/06

    摘要： An engine pylon of an aircraft having a rear portion, two rear cowls around the rear portion, each rear cowl having an upper fixed cowl and a lower movable cowl mounted articulated on the rear portion, wherein in the closed position the two lower movable cowls are moved close to one another, such that their lower edges are contiguous, wherein in the open position the two lower movable cowls are tilted such that their lower edges are moved away from one another, for each lower movable cowl, a hinge system fixed between the lower movable cowl and the rear portion, and at least one locking system which locks the two lower movable cowls to one another in the closed position. The presence of the lower movable cowls ensures, among other things, easy access to the interior of the engine pylon.

    Joint for connecting aircraft structures
    2.
    发明授权
    Joint for connecting aircraft structures 有权

    公开(公告)号：US11161618B2

    公开(公告)日：2021-11-02

    申请号：US16583978

    申请日：2019-09-26

    申请人： AIRBUS OPERATIONS LIMITED ,  AIRBUS OPERATIONS (S.A.S.)

    发明人： William Tulloch ,  Pat Broomfield ,  Olivier Pautis

    IPC分类号： F16M13/00 ,  B64D27/26

    摘要： A joint for connecting a first aircraft structure to a second aircraft structure such that relative rotation and relative translational movement of the first and second aircraft structures along a first axis is permitted, whilst relative translational movement of the first and second aircraft structures along axes orthogonal to the first axis is substantially prevented. The joint includes a bracket having an opening aligned with the first axis; a pin aligned with the first axis and extending through the opening; and a bearing mounted in the opening. The bearing has an inner bearing surface defining a bore through which the pin extends, which is configured for translational sliding contact with the pin, and a part-spherical outer bearing surface configured for rotational sliding contact with the opening.

    Aircraft engine assembly, comprising flexible force transmitting devices radially arranged between the thrust reversal cowls and the engine
    4.
    发明授权
    Aircraft engine assembly, comprising flexible force transmitting devices radially arranged between the thrust reversal cowls and the engine 有权

    公开(公告)号：US10464683B2

    公开(公告)日：2019-11-05

    申请号：US15458567

    申请日：2017-03-14

    申请人： AIRBUS OPERATIONS (S.A.S.)

    发明人： Olivier Pautis ,  Wolfgang Brochard

    IPC分类号： B64D27/18 ,  B64D27/26 ,  B64D29/06

    摘要： To reduce flexural deformations of an engine, an engine assembly comprises a device for attaching the engine onto a structure of an aircraft, the attachment device including a primary structure, an attachment device for attaching the engine onto the primary structure of the attachment pylon, and a nacelle including thrust reversal cowls, each equipped with an inner structure arranged around a case portion of the engine. The assembly includes flexible devices for transmitting forces, arranged between the case portion and the inner structures of the cowls, each device including an elastically deformable device configured so that in the closed position of the cowl, with the engine at a standstill, it adopts a partial elastic deformation state allowing the device to apply a prestress force on the case portion.

    FOLDABLE GUIDING VENTILATOR COVER FOR AN AIRCRAFT ENGINE ASSEMBLY
    6.
    发明申请
    FOLDABLE GUIDING VENTILATOR COVER FOR AN AIRCRAFT ENGINE ASSEMBLY 有权
    用于飞机发动机总成的可折叠导向通风机盖

    公开(公告)号：US20160031563A1

    公开(公告)日：2016-02-04

    申请号：US14811152

    申请日：2015-07-28

    申请人： Airbus Operations S.A.S.

    发明人： Olivier Pautis

    IPC分类号： B64D29/00 ,  F02K1/08 ,  F02K1/18 ,  B64D29/08 ,  B64D27/26

    CPC分类号： B64D29/00 ,  B64C7/02 ,  B64D27/26 ,  B64D29/02 ,  B64D29/06 ,  B64D29/08 ,  F02K1/085 ,  F02K1/18

    摘要： For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively.

    摘要翻译： 为了在空气动力学性能水平方面的增益，飞机发动机组件包括涡轮机，用于涡轮机的紧固支柱以及围绕涡轮机的至少一个折叠通风机盖，其包括：第一盖部分，其包括第一端部， 被安装成沿着第一铰接轴线铰接到紧固支柱，以及第二盖扇区，其包括第一端部，其被安装成铰接到第一盖部分的第二端部，沿着 第二铰接轴线与第一铰接轴线平行。 第二端部分别被安装成通过发动机组件的推力逆变器盖和该组件的进气口结构的一侧而另一侧被引导。

    ASSEMBLY FOR AN AIRCRAFT COMPRISING AN ATTACHMENT PYLON PRIMARY STRUCTURE FORMED WITH THREE INDEPENDENT ELEMENTS
    7.
    发明申请
    ASSEMBLY FOR AN AIRCRAFT COMPRISING AN ATTACHMENT PYLON PRIMARY STRUCTURE FORMED WITH THREE INDEPENDENT ELEMENTS 有权
    装配包含三个独立元件的附件PYLON主要结构的飞机组装

    公开(公告)号：US20150307199A1

    公开(公告)日：2015-10-29

    申请号：US14693545

    申请日：2015-04-22

    申请人： Airbus Operations (S.A.S.)

    发明人： Olivier Pautis ,  Jonathan Blanc

    IPC分类号： B64D29/02 ,  B64D27/18 ,  B64D27/26

    CPC分类号： B64D29/02 ,  B64D27/26 ,  B64D2027/268

    摘要： In order to optimize the bulkiness of a primary structure of an aircraft engine attachment pylon and thus make it easier to install under the wing and as close as possible to the pressure face thereof, the disclosure herein provides an assembly in which the engine comprises a rear part arranged under a wing element equipped with a wing box, the primary structure being made up of the following independent elements: a first and a second side beam arranged one on each side of a vertical mid-plane of the engine; and an intermediate structure through which the vertical mid-plane of the engine passes and which is situated some distance from each of the first and second side beams.

    摘要翻译： 为了优化飞机发动机附件塔的主要结构的蓬松度，并且因此使得更容易安装在机翼下方并且尽可能靠近其压力面，本文的公开内容提供了一种组件，其中发动机包括后部 所述主体结构由以下独立元件构成：第一和第二侧梁，其布置在所述发动机的垂直中平面的每一侧上; 以及中间结构，发动机的垂直中间平面通过该中间结构，并且与第一和第二侧梁中的每一个相距一定距离。