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公开(公告)号：US20220033098A1
公开(公告)日：2022-02-03
申请号：US17386966
申请日：2021-07-28
Applicant: Airbus Operations (S.A.S.)
Inventor： Laurent Frenot , Olivier Pautis , Michael Berjot , Thomas Robiglio , Germain Gueneau
Abstract: A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.
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公开(公告)号：US10669970B2
公开(公告)日：2020-06-02
申请号：US16007006
申请日：2018-06-13
Applicant: Airbus Operations S.A.S.
Inventor： Olivier Pautis , Lionel Czapla
Abstract: A thrust reverser system includes two thrust reversal cascades, of which the first cascade is entrained by an actuator, and which are configured to adopt a retracted position in which they are housed in a space located outside the duct. The action of the actuator brings about: rearward displacement of the first cascade in the direction of a nacelle opening; and during part of the rearward displacement of the second cascade, simultaneous pivoting of this second cascade under the action of a control lever, the interaction of which with a fixed guide rail forces the front end of the lever to move radially inwards while the lever is entrained rearwards by the second cascade.
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23.发明申请公开(公告)号：US20200148378A1
公开(公告)日：2020-05-14
申请号：US16603988
申请日：2018-04-09
Applicant: Airbus Operations S.A.S.
Inventor： Olivier Pautis , Laurent Lafont , Rohan Nanda
Abstract: In order to bring the primary structure of an engine mounting pylon of an aircraft as close as possible to a wing box: —an aircraft wing includes a wing box made partly by a front spar and an intermediate spar; —a mounting pylon including a primary structure in the form of a box having transverse reinforcement ribs; and —attachment means for attaching the primary structure of the mounting pylon on the wing box. These attachment means include a row of bolts along which each bolt passes through a structural part of the pylon on one hand, and on the other hand a fitting attached to one of the front and intermediate spars.
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Patent Agency Ranking
公开(公告)号：US20200087000A1
公开(公告)日：2020-03-19
申请号：US16560023
申请日：2019-09-04
Applicant: Airbus Operations S.A.S.
Inventor： Pascal Martinez , Olivier Pautis
Abstract: A method for mounting an aircraft pylon connected to a wing includes: a step of pre-positioning first and second contact surfaces respectively provided on the wing and the pylon, a step of installing and tightening temporary connection elements, so as to keep the first and second contact surfaces clamped against one another, a step of installing and expanding at least one radially expandable element in at least one pair of first and second receptacles respectively provided on the wing and the pylon, a step of installing and tightening final connection elements connecting the pylon and the wing in the mounted state, a step of removing the radially expandable element(s) and the temporary connection elements, and of installing the remaining final connection elements and shear pin(s).
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公开(公告)号：US10562639B2
公开(公告)日：2020-02-18
申请号：US15381821
申请日：2016-12-16
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Olivier Pautis , Jean-Michel Rogero
Abstract: In order to reduce congestion of attachments between an aircraft engine and its attachments, an engine assembly is provided, the primary structure of the device of which includes a structural cover surrounding the engine and connected on a central box, the cover including an outer skin interiorly delimiting a secondary flow. A group of main mounts is provided as a group of secondary mounts laid out at the rear of the group of main mounts, the group of main mounts including a plurality of bolts distributed around the longitudinal axis of the engine and ensuring the attachment of a front end of the cover to the hub of the intermediate case, and a group of secondary mounts including a plurality of secondary mounts distributed around the axis and ensuring attachment of a rear portion of the engine to a rear end of the cover.
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26.发明申请公开(公告)号：US20190283890A1
公开(公告)日：2019-09-19
申请号：US16352332
申请日：2019-03-13
Applicant: Airbus Operations (S.A.S.)
Inventor： Olivier Pautis , Jérôme Colmagro , Jonathan Blanc
IPC: B64D27/26
Abstract: A primary structure of a strut for bearing an aircraft power plant including a front part intended to be joined to an aircraft power plant and a rear part intended to be joined to a structure of the aircraft, the front part being formed from a box including an upper longitudinal member, a lower longitudinal member, and lateral panels. A main rib is located at an interface between the front part and the rear part. The rear part is formed from a set of four connecting rods. The first end of each connecting rod is joined to the front part of the primary structure and the second end of each connecting rod is joined to a separate interface for fastening to the structure of the aircraft. This allows a substantial simplification of the primary structure of a strut for bearing an aircraft power plant, which can have advantages in particular in terms of cost, mass, and simplicity of implementation and integration.
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公开(公告)号：US09783314B2
公开(公告)日：2017-10-10
申请号：US14811152
申请日：2015-07-28
Applicant: Airbus Operations S.A.S.
Inventor： Olivier Pautis
CPC classification number: B64D29/00 , B64C7/02 , B64D27/26 , B64D29/02 , B64D29/06 , B64D29/08 , F02K1/085 , F02K1/18
Abstract: 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.
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公开(公告)号：US20160130009A9
公开(公告)日：2016-05-12
申请号：US14693545
申请日：2015-04-22
Applicant: Airbus Operations (S.A.S.)
Inventor： Olivier Pautis , Jonathan Blanc
CPC classification number: B64D29/02 , B64D27/26 , B64D2027/268
Abstract: 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.
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