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    ENGINE PYLON FOR COUPLING A JET ENGINE TO A WING OF AN AIRCRAFT
    1.
    发明公开
    ENGINE PYLON FOR COUPLING A JET ENGINE TO A WING OF AN AIRCRAFT 审中-公开

    公开(公告)号：US20230159179A1

    公开(公告)日：2023-05-25

    申请号：US17988862

    申请日：2022-11-17

    Applicant: Airbus Operations SAS

    Inventor： Olivier PAUTIS ,  Jonathan BLANC

    IPC: B64D27/26 ,  F01D25/28

    CPC classification number: B64D27/26 ,  F01D25/28 ,  B64D2027/262 ,  B64D27/16

    Abstract: An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.

    BRACED-PYLON ARCHITECTURE FOR MOUNTING AN ENGINE TO AN AIRCRAFT
    2.
    发明申请
    BRACED-PYLON ARCHITECTURE FOR MOUNTING AN ENGINE TO AN AIRCRAFT 有权

    公开(公告)号：US20220127010A1

    公开(公告)日：2022-04-28

    申请号：US17509113

    申请日：2021-10-25

    Applicant: Airbus Operations SAS

    Inventor： Olivier PAUTIS ,  Jérôme COLMAGRO

    IPC: B64D27/26

    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.

    NACELLE OF A TURBOJET COMPRISING A REVERSER FLAP AND A DEPLOYMENT SYSTEM WITH DELAY
    3.
    发明申请
    NACELLE OF A TURBOJET COMPRISING A REVERSER FLAP AND A DEPLOYMENT SYSTEM WITH DELAY 审中-公开

    公开(公告)号：US20200240360A1

    公开(公告)日：2020-07-30

    申请号：US16714986

    申请日：2019-12-16

    Applicant: Airbus Operations SAS

    Inventor： Olivier PAUTIS

    IPC: F02K1/72 ,  F02K1/08

    Abstract: A bypass turbojet nacelle comprising a fixed structure, a fixed cowl and a cowl movable in translation between advanced and withdrawn positions by a ram with a reverser flap movable thereon, and a deployment system comprising a first slider integral with the movable cowl, a first groove comprising a first part and a curved, second part integral with the fixed structure, a second slider movable in translation in the second groove part, a first connecting rod rotatable on the first slider and on the second slider, and a second connecting rod articulated on both the first connecting rod first end and the reverser flap. The ram rod is articulated on the first connecting rod. Moving the first slider from the advanced to the withdrawn position moves the second slider along the first part and, when the first slider reaches the withdrawn position, the second slider moves along the second part.

    AIRCRAFT HAVING AN ENGINE PYLON WITH A MOBILE COWL
    5.
    发明公开
    AIRCRAFT HAVING AN ENGINE PYLON WITH A MOBILE COWL 审中-公开

    公开(公告)号：US20240199218A1

    公开(公告)日：2024-06-20

    申请号：US18541513

    申请日：2023-12-15

    Applicant: Airbus Operations SAS

    Inventor： Olivier PAUTIS ,  Paolo MESSINA ,  Jonathan BLANC ,  Thomas ROBIGLIO ,  Thomas FIRMIGNAC

    IPC: B64D29/06 ,  B64D29/02

    CPC classification number: B64D29/06 ,  B64D29/02

    Abstract: An aircraft having a fixed structure, an engine pylon, and a cowling system, a slider bearing a rear cowl and able to move in translation from an advanced position to a retracted position, a displacement system having, on either side of a median plane of the engine pylon, a guide as one with the fixed structure, a sliding element as one with the slider and sliding along each guide disposed on the same side, and a support as one with the fixed structure and having a blade parallel to the translation direction and on which a surface parallel to the translation direction of the slider rests. The presence of the mobile cowl ensures, inter alia, easy access to the inside of the engine pylon and to the systems that are housed therein.

    SHACKLE FOR FASTENING AN AIRCRAFT ENGINE COMPRISING A PAIR OF ENCAPSULATED ANTI-FRICTION COATINGS, AND AIRCRAFT COMPRISING SUCH A SHACKLE
    6.
    发明申请
    SHACKLE FOR FASTENING AN AIRCRAFT ENGINE COMPRISING A PAIR OF ENCAPSULATED ANTI-FRICTION COATINGS, AND AIRCRAFT COMPRISING SUCH A SHACKLE 有权

    公开(公告)号：US20230002067A1

    公开(公告)日：2023-01-05

    申请号：US17851407

    申请日：2022-06-28

    Applicant: Airbus Operations SAS

    Inventor： Cédric POUPON ,  Olivier PAUTIS ,  Jonathan BLANC

    IPC: B64D27/26 ,  F16C11/06

    Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

    ASSEMBLY FOR A NACELLE OF AN AIRCRAFT ENGINE, SAID ASSEMBLY COMPRISING A FIXED COWL AND A COWL MOUNTED SO AS TO BE ABLE TO MOVE ON THE FIXED COWL
    8.
    发明申请
    ASSEMBLY FOR A NACELLE OF AN AIRCRAFT ENGINE, SAID ASSEMBLY COMPRISING A FIXED COWL AND A COWL MOUNTED SO AS TO BE ABLE TO MOVE ON THE FIXED COWL 有权

    公开(公告)号：US20230040055A1

    公开(公告)日：2023-02-09

    申请号：US17878360

    申请日：2022-08-01

    Applicant: Airbus Operations SAS

    Inventor： Umberto GASTALDI ,  Wolfgang BROCHARD ,  Olivier PAUTIS

    IPC: 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.

    ASSEMBLY FOR AN AIRCRAFT, THE ASSEMBLY HAVING A PYLON AND A WING
    9.
    发明申请
    ASSEMBLY FOR AN AIRCRAFT, THE ASSEMBLY HAVING A PYLON AND A WING 有权

    公开(公告)号：US20220204155A1

    公开(公告)日：2022-06-30

    申请号：US17502417

    申请日：2021-10-15

    Applicant: Airbus Operations SAS

    Inventor： Paolo MESSINA ,  Olivier PAUTIS

    IPC: B64C3/32 ,  B64F5/10

    Abstract: An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

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