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211.发明公开公开(公告)号：US20230249798A1
公开(公告)日：2023-08-10
申请号：US18163399
申请日：2023-02-02
Applicant: Airbus Operations (S.A.S.)
Inventor： Jérôme Milliere
Abstract: A skidding phase shock absorber and protection device to protect a part on an aircraft for example at the level of a fuel tank of the aircraft includes a support and a convex plate to assume a first position and a second position and to in the first position, because of the action of compression forces, undergo resisted plastic deformation via an elastic element and in a second position to withstand friction, the device assuring, during a crash landing of the aircraft with an impact phase followed by a skidding phase, both protection against the compression forces generated during the impact phase, via the plastic deformation and the elastic shock absorption, and mechanical protection and protection against heating during the skidding phase.
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212.发明公开公开(公告)号：US20230192318A1
公开(公告)日：2023-06-22
申请号：US18065741
申请日：2022-12-14
Applicant: Airbus Operations (S.A.S.)
Inventor： Damien Aguera , Arnaud Tonnele , Salim Chalqi , Yannick Lampure , Alain Mady
CPC classification number: B64F5/10 , B64C1/18 , B64C1/069 , B64C1/0683
Abstract: An assembly method includes a succession of assembly steps of assembling fuselage components of the fuselage portion of the aircraft, for example the nose of the aircraft, to form a fuselage body, a mounting step of introducing, into the fuselage body thus formed, a floor module having at least a predetermined width, and which can be provided with items of equipment, and a fastening step of fastening the fuselage body to the floor module such that the floor module shapes the final shape of the fuselage body and the assembled fuselage portion is obtained, the floor module, which has at least a suitable predetermined width, making it possible, when it is incorporated into the fuselage body, to provide the fuselage body, which is slightly flexible, with its desired and definitive shape corresponding to the desired and definitive shape of the assembled fuselage portion.
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213.发明公开公开(公告)号：US20230184194A1
公开(公告)日：2023-06-15
申请号：US17870255
申请日：2022-07-21
Applicant: Airbus Operations (S.A.S.)
Inventor： Thierry Gaches , Laurent Cazeaux
Abstract: An assembly includes a structure with 6 o'clock and 12 o'clock beams and front and rear curved beams, in which the 12 o'clock beam is mounted to be able to rotate on a pylon of an aircraft between a closed position and a raised position, a fan cowl fixed to the structure, a thrust reverser with a rear cowl and that is able to move in translation along the 6 o'clock and 12 o'clock beams between a forward position and a backward position, cascades fixed to the thrust reverser, and a mover for moving the thrust reverser. With such an arrangement, the fan cowl and the thrust reverser are fixed to the same structure, and it is this structure that is hinged to the pylon.
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公开(公告)号：US11661169B2
公开(公告)日：2023-05-30
申请号：US17129175
申请日：2020-12-21
Applicant: Airbus (S.A.S.) , Airbus Operations (S.A.S.)
Inventor： Christian Godenzi , Jean-Michel Corvi , Thomas Sanpons
IPC: B64C1/18
CPC classification number: B64C1/18
Abstract: A floor structure for an aircraft includes a rail that defines a recess having an opening and a bottom and designed to receive one or more attachment elements, a covering element arranged above a segment of the recess so as to provide a complementary bearing surface above the opening, and a cellular supporting structure having a first end that rests on the bottom of the recess, and a second end supporting the covering element. Thus, the covering element can be sufficiently thin to avoid or limit the formation of steps at the surface of the floor structure.
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公开(公告)号：US11643214B2
公开(公告)日：2023-05-09
申请号：US17149289
申请日：2021-01-14
Applicant: Airbus Operations (S.A.S.)
Inventor： Michael Berjot , Julien Cayssials , Adeline Soulie
CPC classification number: B64D13/00 , B64D2013/0618 , F16K1/2021 , F16K1/223 , F16K31/521
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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Patent Agency Ranking
公开(公告)号：US20230132606A1
公开(公告)日：2023-05-04
申请号：US17973957
申请日：2022-10-26
Applicant: Airbus Operations (S.A.S.)
Inventor： Laurent Talou , Yannick Kaufling
Abstract: A particle suction nozzle including a body that has a suction mouth as well as at least a portion of a fastening system designed to link the nozzle to a support. The fastening system has at least one tubular insert made of elastically deformable material rigidly connected to the body and designed to be fitted onto a linking element rigidly connected to the support, and once fitted, to be immobilized in relation to the linking element and at a distance from the support. A suction device includes the suction nozzle.
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公开(公告)号：US20230101231A1
公开(公告)日：2023-03-30
申请号：US17952599
申请日：2022-09-26
Applicant: Airbus Operations (S.A.S.)
Inventor： Herve Tressol , Sébastien Forasacco
Abstract: A guide system to enable installation of a cable tie on a supporting element by passing the cable tie through a first passage to traverse the supporting element, then through a second passage to come back to the same side of the supporting element, enabling the cable tie to surround one or more cables. The guide device includes a gutter with a guide surface with two curves, a first longitudinal curve enabling the surface to extend from a passage to the other passage and a second transverse curve forming a partial envelope for receiving the cable tie and guiding and holding the cable tie in the gutter. The device also has at least one protrusion with a wedging surface projecting from the surface of the gutter to come into contact with and wedge against the supporting element to lock the gutter in position in relation to the supporting element.
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公开(公告)号：US11591098B2
公开(公告)日：2023-02-28
申请号：US16226910
申请日：2018-12-20
Applicant: Airbus Operations S.A.S.
Inventor： Frédéric Vinches , Arnaud Bourhis , Julien Sentier , Clément Breton
Abstract: A nacelle forward part of an aircraft propulsion assembly, includes an air inlet lip at the front end, an internal structure and an external panel extending the lip, and an annular stiffening frame formed around an axis of revolution and comprising an internal peripheral edge linked to the internal structure and an external peripheral edge linked to the external panel. The stiffening frame presents an inclination relative to the axis of revolution, its slope being oriented towards the front end of the nacelle forward part. The stiffening frame is configured to deviate, outside the nacelle of the propulsion assembly, an object striking the stiffening frame. The stiffening frame so configured is capable of withstanding the impacts of objects without breaking while enabling the object striking the stiffening frame to be deviated towards the exterior of the nacelle.
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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.
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公开(公告)号：US20220411038A1
公开(公告)日：2022-12-29
申请号：US17849889
申请日：2022-06-27
Applicant: Airbus Operations (S.A.S.)
Inventor： Omar Molina Hamdan , Valérie Lavigne , Jérôme Dubost
Abstract: A linking member between a first and a second structural member of a fuselage of an aircraft allowing improved dissipation of stresses. The linking member has a first part made of a solid structure and at least one second part made of a lattice structure. The first part made of the solid structure is configured to dissipate static stresses and to withstand fatigue up to a predetermined maximum stress and fatigue threshold. This configuration allows improved dissipation of the stresses exerted on the linking member.
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