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    Assembly for an aircraft having a wing and an engine pylon for coupling a jet engine to said wing
    11.
    发明授权
    Assembly for an aircraft having a wing and an engine pylon for coupling a jet engine to said wing 有权

    公开(公告)号：US11572186B2

    公开(公告)日：2023-02-07

    申请号：US17375393

    申请日：2021-07-14

    Applicant: Airbus Operations SAS

    Inventor： Germain Gueneau ,  Michael Berjot ,  Olivier Pautis

    IPC: B64D27/26 ,  B64C3/32 ,  B64D27/16 ,  B64C3/18

    Abstract: An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

    Thrust reverser system limiting aerodynamic perturbation in an inactive configuration
    14.
    发明授权
    Thrust reverser system limiting aerodynamic perturbation in an inactive configuration 有权

    公开(公告)号：US10519899B2

    公开(公告)日：2019-12-31

    申请号：US15693735

    申请日：2017-09-01

    Applicant: Airbus Operations (SAS)

    Inventor： Olivier Pautis ,  Jerome Colmagro

    IPC: F02K1/72 ,  F02K1/76

    Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.

    Braced-pylon architecture for mounting an engine to an aircraft
    15.
    发明授权
    Braced-pylon architecture for mounting an engine to an aircraft 有权

    公开(公告)号：US11840348B2

    公开(公告)日：2023-12-12

    申请号：US17509113

    申请日：2021-10-25

    Applicant: Airbus Operations SAS

    Inventor： Olivier Pautis ,  Jérôme Colmagro

    IPC: F02C7/20 ,  B64D27/26

    CPC classification number: B64D27/26 ,  F02C7/20 ,  B64D2027/264 ,  B64D2027/266 ,  B64D2027/268

    Abstract: An engine mounting pylon for suspending a turbofan beneath an aircraft wing, including a primary structure, a fastening device for fastening to the turbofan, and a fastening device for fastening to the wing. The engine mounting pylon furthermore comprises multiple rigid braces that mechanically connect the primary structure to the wing of the aircraft, a first brace-attachment device that mechanically connects a first end of each brace to the wing, and a second brace-attachment device that mechanically connects a second end of each brace to the primary structure. This braced-pylon architecture makes it possible to reduce the dimensions of the primary structure and the various elements that constitute the first and second attachment devices.

    Assembly for an aircraft, the assembly comprising a mast and a wing
    16.
    发明授权
    Assembly for an aircraft, the assembly comprising a mast and a wing 有权

    公开(公告)号：US11753177B2

    公开(公告)日：2023-09-12

    申请号：US17621467

    申请日：2020-06-09

    Applicant: Airbus Operations SAS

    Inventor： Olivier Pautis ,  Michael Berjot

    IPC: B64D27/26 ,  B64C3/18

    CPC classification number: B64D27/26 ,  B64C3/185 ,  B64D2027/262

    Abstract: An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

    PROPULSION ASSEMBLY INCORPORATING A TURBOJET AND A MOUNTING PYLON ENABLING A NEW DISTRIBUTION OF THE FORCES BETWEEN THE TURBOJET AND THE WING
    20.
    发明申请
    PROPULSION ASSEMBLY INCORPORATING A TURBOJET AND A MOUNTING PYLON ENABLING A NEW DISTRIBUTION OF THE FORCES BETWEEN THE TURBOJET AND THE WING 有权
    装配涡轮机和安装螺旋桨的推进装置启动了涡轮机和风力之间的力量的新分配

    公开(公告)号：US20160221682A1

    公开(公告)日：2016-08-04

    申请号：US15008593

    申请日：2016-01-28

    Applicant: Airbus Operations SAS

    Inventor： Olivier Pautis ,  Rohan Nanda

    IPC: B64D27/26 ,  B64D27/18

    CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/262 ,  B64D2027/268

    Abstract: A propulsion assembly includes a turbojet incorporating a fan casing and a central casing around a longitudinal axis, a mounting pylon having a rigid structure, a forward engine attachment interposed between a forward extremity of the rigid structure and an upper part of the fan casing, the upper part being in a vertical median plane (P) passing through the longitudinal axis, an aft engine attachment interposed between a median zone of the rigid structure and an upper aft part of the central casing, and a device for absorbing the thrust forces generated by the turbojet, including two links placed either side of the median plane (P) and hinged, on one hand, forward, on a forward part of the central casing, and on the other, aft, directly on the rigid structure. Such an arrangement enables a reduction of the stresses, and the possibility of designing a simplified rigid structure.

    Abstract translation: 推进组件包括涡轮喷气发动机，其包括风扇壳体和围绕纵向轴线的中心壳体，具有刚性结构的安装支架，插入在刚性结构的前端和风扇壳体的上部之间的前部发动机附件， 上部位于通过纵向轴线的垂直中间平面（P）中，插入在刚性结构的中间区域和中央壳体的上部后部之间的后部发动机附件，以及用于吸收由中心壳体产生的推力的装置， 涡轮喷气发动机，包括位于中间平面（P）的任一侧的两个连杆，并且一方面在中心壳体的前部向前并且另一个直接在刚性结构上的后部铰接。 这种布置使得能够减小应力，并且可以设计简化的刚性结构。

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