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公开(公告)号：US20220106978A1
公开(公告)日：2022-04-07
申请号：US17477981
申请日：2021-09-17
Applicant: Airbus Operations S.A.S.
Inventor： Simon Foucart-Gaudy , Vincent Delpy , Gerard Millet
Abstract: A seal includes a barrel extending between a base and a top, in which the barrel has a cylindrical cavity passing through it between its base and its top, and a skirt indissociable from the barrel and extending around said barrel, in which the skirt adopts the shape of a dome of which the exterior edges extend out beyond the base starting from the top. The seal is able to divert the fluid and keep the space under the skirt fluid tight.
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232.发明申请公开(公告)号：US20220097870A1
公开(公告)日：2022-03-31
申请号：US17487617
申请日：2021-09-28
Applicant: Airbus Operations (S.A.S.)
Inventor： Cédric Godard , Florian Collado , Jacques Bouriquet , Jean-Marc Datas , Nicolas Darbonville , André Aquila
Abstract: A facility for simplifying the facilities and tools required to assemble a first aircraft fuselage section and a second aircraft fuselage section by the ends thereof, these sections being fragile, large elements. The facility includes a logistics trolley that can be moved on the floor and immobilized in a position to carry the first section, at least one adjustable support installed on the floor at another position that is adjustable with six degrees of freedom, to carry the second section. Each support can be commanded to adjust the position of the second section in relation to the first section, such as to position one end of the second section in geometric conformity with one end of the first section. This arrangement enables all movements to be made directly on the floor, obviating the need to provide lifting machines or overhead traveling cranes within the assembly facility.
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233.发明授权公开(公告)号：US11289901B2
公开(公告)日：2022-03-29
申请号：US16074182
申请日：2017-02-17
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Wolfram Birkmayer
Abstract: A direct current electrical network includes nodes linked by branches and protection elements mounted on the branches, each protection element includes a central processing unit, a current sensor, a current limiter device and a circuit breaking device, wherein: the current sensor is configured to determine the direction of the current in the branch relative to the node with which said protection element is associated; the central processing unit is configured to select, as a function of the direction of the current, a selected threshold value as one of a first value or a second threshold value greater than the first threshold value in absolute value, and to compare the value of the intensity of the current to the selected threshold value; and the current limiter device is bidirectional and is configured to limit the current passing through the branch to the selected threshold value.
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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：US20210374996A1
公开(公告)日：2021-12-02
申请号：US17328441
申请日：2021-05-24
Applicant: Airbus (S.A.S.) , Airbus Operations (S.A.S.)
Inventor： Philippe Foucault , Maxime Lefort , Quentin Demoulin
Abstract: The method includes a step of acquisition of an image of the leading aircraft, a step of extraction of the outline, an adjustment step including implementing an outline registration algorithm, to determine an optimized profile from a comparison of the outline of the leading aircraft with a profile of the leading aircraft determined from a three-dimensional model of the leading aircraft and from an initial position of the following aircraft with respect to the leading aircraft, and a step of determination of the positioning according to six degrees of freedom of the following aircraft with respect to the leading aircraft, from the optimized profile and from the three-dimensional model of the leading aircraft. The method thus makes it possible to rapidly and accurately determine the positioning of the following aircraft with respect to the leading aircraft, this positioning being used to implement a formation flight.
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Patent Agency Ranking
236.发明申请公开(公告)号：US20210353986A1
公开(公告)日：2021-11-18
申请号：US17318684
申请日：2021-05-12
Applicant: Airbus Operations (S.A.S.)
Inventor： Thierry Clavel , Stéphane Pugliese , Arnaud Guichot , Nicolas Brachet
Abstract: An aircraft with at least one propulsion assembly and its fire-fighting system, which includes two reservoirs of extinguishing agent, and, associated with each reservoir, a control that can be actuated by a pilot to open the reservoir, a detection assembly to detect a fire and emit, if appropriate, a fire alert signal, the propulsion assembly including a first and a second compartment each including at least one fire zone, the fire-fighting system including a bypass valve controlled by a localization unit, a set of pipes connecting each reservoir to each of the fire zones through the bypass valve, the localization unit configured to detect a fire in a fire zone in the first compartment, and, if appropriate, control the bypass valve so it adopts a first state where the extinguishing agent in a reservoir is expelled towards the one or more fire zones in the first compartment after activation of the control associated with a reservoir, the bypass valve otherwise being controlled to adopt a second state, in which the extinguishing agent in a reservoir is expelled towards the one or more fire zones in the second compartment.
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公开(公告)号：US11167838B2
公开(公告)日：2021-11-09
申请号：US16417744
申请日：2019-05-21
Applicant: Airbus Operations (S.A.S.)
Inventor： Bernard Guering , Laurent Saint-Marc
Abstract: A rudder control unit includes a single-piece main module mobile on a curved support frame. The rudder control unit includes a curved support and guide frame to be mounted in a floor of the aircraft, and a unique main module including the pedals and a set of functionalities, the main module configured such that it is movable and positioned on the support and guide frame using a movement unit, thus making it possible to obtain an extremely simplified architecture with a reduced number of pieces.
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公开(公告)号：US20210214089A1
公开(公告)日：2021-07-15
申请号：US17149289
申请日：2021-01-14
Applicant: Airbus Operations (S.A.S.)
Inventor： Michael Berjot , Julien Cayssials , Adeline Soulie
IPC: B64D13/00
Abstract: A cold regulating valve for a heat exchanger system of an aircraft propulsion system, where the cold regulating valve includes an open frame which delimits an opening, two shutters with an external convex shape slidably mounted on the open frame between a closed position and an open position, a mechanism linked to the shutters and mobile between a first position and a second position, and wherein the mechanism moves the shutters from the closed position to the open position when it moves from the first position to the second position and vice versa, and an actuator acting on the mechanism to move it from the first position to the second position and vice versa. The specific embodiment of the cold regulating valve generates a low drag when the shutters are in a closed position.
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公开(公告)号：US11048833B2
公开(公告)日：2021-06-29
申请号：US15964316
申请日：2018-04-27
Applicant: Airbus Operations (S.A.S.)
Inventor： Milan Tasic
Abstract: A method of calibrating stiffness of support structures of an assembly including a main structure and support structures includes modeling the assembly using finite elements, with a theoretical stiffness of the support structures, in moderate support load conditions, calculating calculated reaction forces for each support structure and measuring corresponding measured reaction forces. The stiffness of each support structure is calibrated by determining a calculated stiffness of each support structure based on comparison between the calculated reaction forces and the measured reaction forces. The modeling and simple measurements during an operational phase, in which the support loads are moderate, thus enable the calibration of the stiffness of the support structures. An associated method of modeling the assembly and a corresponding computer program are also disclosed.
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240.发明授权公开(公告)号：US11045931B2
公开(公告)日：2021-06-29
申请号：US16224338
申请日：2018-12-18
Applicant: Airbus Operations Ltd. , Airbus Operations (S.A.S.)
Inventor： David Petit , Geneviève Schubetzer , Damien Fraysse , Serge Vernet , Sophie Gourdon , Nicolas Charmes , Mathieu Trindade , Joel Antic
Abstract: When coupling tubular parts by fitting, the seal interposed between them may roll on itself, be pinched or damaged. Now, a twisted or damaged seal no longer correctly ensures the seal-tightness and it is very difficult to detect this. The present application discloses a tool for installing a seal between two tubular parts, one male and one female, including a compression ring to encircle the male part and exert a compression on the seal before producing the join. The tool also includes a tongue that can be positioned at a chamfered surface of the female tubular part. The tongue makes it possible to offer the pre-compressed seal with the dimensions of the female part a continuous travel making it possible to prevent any twisting or other effect compromising the seal-tightness.
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