-
11.发明授权公开(公告)号：US10246196B2
公开(公告)日：2019-04-02
申请号：US15285211
申请日：2016-10-04
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Olivier Pautis , Wolfgang Brochard
Abstract: In order to reduce the width of the attachment between the rear portion of an aircraft engine and its attachment pylon, an engine assembly attachment include an assembly of rear engine attachments comprising a first connecting rod laid out in a longitudinal and median vertical plane, a second connecting rod substantially laid out tangentially to the inter-turbine case, and a rear engine attachment for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods, and comprising a shear pin oriented along a vertical direction of the engine assembly.
-
12.发明授权公开(公告)号：US10232930B2
公开(公告)日：2019-03-19
申请号：US15067854
申请日：2016-03-11
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Olivier Pautis , Jérôme Colmagro
Abstract: In order to reduce the risks of movable nacelle cowlings opening, the invention provides a nacelle for an aircraft engine assembly comprising a fixed nacelle structure as well as at least one jointed movable cowling on the fixed structure, the cowling being jointed at its front end on the fixed structure so that, upon closing the movable cowling, a rear end of this cowling moves towards the rear and radially towards the inside.
-
公开(公告)号：US20190003420A1
公开(公告)日：2019-01-03
申请号：US16001331
申请日：2018-06-06
Applicant: Airbus Operations S.A.S.
Inventor： Olivier Pautis
Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.
-
公开(公告)号：US20180372024A1
公开(公告)日：2018-12-27
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.
-
公开(公告)号：US11332255B2
公开(公告)日：2022-05-17
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.
-
Patent Agency Ranking
公开(公告)号：US11208215B2
公开(公告)日：2021-12-28
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).
-
公开(公告)号：US10731602B2
公开(公告)日：2020-08-04
申请号：US16001331
申请日：2018-06-06
Applicant: Airbus Operations S.A.S.
Inventor： Olivier Pautis
Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.
-
公开(公告)号：US09889942B2
公开(公告)日：2018-02-13
申请号：US15015841
申请日：2016-02-04
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Olivier Pautis , Wolfgang Brochard
Abstract: In order to optimize the bulk of a primary structure of an aircraft engine attachment pylon, and to favor the installation of the engine as close as possible to the wing element, the disclosure herein provides an aircraft assembly comprising a wing element, a turbofan engine and an engine attachment pylon, the engine comprising a rear part arranged under the wing element equipped with a wing structure, the pylon comprising a primary structure for transmitting loads from the engine to the wing structure, this primary structure comprising a pylon box, and the assembly also comprising an attachment for attaching the primary structure to the engine. According to the disclosure herein, the wing structure comprises two wing boxes that follow one another in a wingspan direction of the wing element, and the pylon box is arranged between these boxes and fixed to each of the latter.
-
公开(公告)号：US11554872B2
公开(公告)日：2023-01-17
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.
-
公开(公告)号：US20220355945A1
公开(公告)日：2022-11-10
申请号：US17733065
申请日：2022-04-29
Applicant: Airbus Operations (S.A.S.)
Inventor： Paolo Messina , Olivier Pautis
IPC: B64D27/26
Abstract: An assembly includes a rear engine attachment having a joining part, and also at least one support connected to the joining part by a connecting system. A lower spar of a primary structure of an aircraft pylon has a central part and also first and second lips disposed on either side of the central part and oriented in the direction of the rear engine attachment. The support has a base connected to the central part of the lower spar, at least one transverse flange supporting the connecting system and also at least one longitudinal flange connected to the base, pressed against the first or second lip of the lower spar and connected to the latter by at least one lateral connecting element.
-
-
-
-
-
-
-
-
-
Search Results
28
records
(took 0.014 seconds)
