公开(公告)号：US20250145273A1

公开(公告)日：2025-05-08

申请号：US18940592

申请日：2024-11-07

Applicant: AIRBUS OPERATIONS, S.L.U.

Inventor： Alvaro JARA RODELGO ,  Miguel GONZALEZ ANTOHI ,  Mikel DE LA PUERTA VALLEJO

IPC: B64C3/18 ,  B29C70/46 ,  B29L31/30

Abstract: A double Y-shaped cross-section spar (100) for an aircraft torsion box including a spar web (110) having an I-shaped cross-section, an upper part connected by the spar web (110), a lower part including lower flanges (130a, 130b) configured to be connectable to a first panel (1010) of the torsion box, a first cross-section opened triangular-shaped structure (120) including first and second lower vertices (120a, 120b) respectively joined to the lower flanges (130a, 130b) and an upper vertex (120c) connected to a first end of the spar web (110) and the upper part comprising upper flanges (130c, 130d) connectable to a second panel (1020) panel of the torsion box, a second cross-section opened triangular-shaped structure (140) including first and second upper vertices (140a, 140b) respectively joined to the upper flanges (130c, 130d) and a lower vertex (140c) connected to a second end of the spar web (110).

公开(公告)号：US20250100706A1

公开(公告)日：2025-03-27

申请号：US18896119

申请日：2024-09-25

Applicant: Airbus Operations S.L.U.

Inventor： Juan Luis MARCOS IZQUIERDO

IPC: B64D37/32 ,  B01F23/10 ,  B01F25/51 ,  B01F35/21 ,  B01F35/60 ,  B01F35/71 ,  B01F35/75 ,  B01F101/59 ,  B64D37/30 ,  H01M8/04

Abstract: An inerting system for an aircraft and a method of inerting a hydrogen system in an aircraft. Also an aircraft with such an inert system. In the inerting system, a part of an inerting gas that has already been supplied to the casing of the hydrogen system is mixed with pure inerting gas through a fluid recirculation system.

公开(公告)号：US20240326235A1

公开(公告)日：2024-10-03

申请号：US18194027

申请日：2023-03-31

Applicant: Airbus Operations GmbH ,  Airbus Operations S.L.U.

Inventor： Chace FADLOVICH ,  Michael WOOGERD ,  Eric POSPISIL ,  Mike GRIMSTAD ,  Joseph BERRY ,  Juan Francisco GARCIA AMADO

IPC: B25J5/04 ,  B23Q7/00 ,  B64F5/10

CPC classification number: B25J5/04 ,  B23Q7/001 ,  B64F5/10

Abstract: An apparatus for performing operations on a part, and in particular on the fuselage of an aircraft. The apparatus utilizes movable arches which carry an and effector and which move along a track fixed to a structure. Additional, fixed arches are positioned at specific longitudinal positions and when the movable arches are aligned with the fixed arches, the end effector may move from the movable arch to the fixed arch.

公开(公告)号：US20240271576A1

公开(公告)日：2024-08-15

申请号：US18529072

申请日：2023-12-05

Applicant: Airbus Operations S.L.U.

Inventor： Carlos CASADO MONTERO ,  Pablo Manuel CALDERÓN GÓMEZ

IPC: F02C9/28 ,  B64D41/00 ,  F02C7/224 ,  F23R3/28

CPC classification number: F02C9/28 ,  B64D41/00 ,  F02C7/224 ,  F23R3/28 ,  F05D2270/301 ,  F05D2270/303

Abstract: An aircraft conditioning system including a fuel tank, including an outlet connected to an Auxiliary Power Unit (APU) fuel inlet, configured to maintain a pressurized gas fuel, a pressure regulator, downstream of the fuel tank, configured to regulate a pressure of the pressurized gas fuel injected to the APU inlet, a first temperature sensor downstream of the pressure regulator and a second temperature sensor upstream of an engine, a first pressure sensor inside the fuel tank, a second pressure sensor downstream of the pressure regulator and a third pressure sensor at an engine inlet, and a controller connected to the pressure sensors and the temperature sensors, the controller receiving temperature and pressure values from the pressure sensors and from the temperature sensors and actuating on at least one of the pressure regulator or the injection position of the pressurized gas fuel inside a plurality of engine combustion chambers.

公开(公告)号：US20240190581A1

公开(公告)日：2024-06-13

申请号：US18523042

申请日：2023-11-29

Applicant: AIRBUS OPERATIONS, S.L.U.

Inventor： Benjamin DAVID ,  Marcos Javier CHIABRANDO ,  María Cruz ZAMARRO MARTÍN ,  Francisco Manuel ANDREU FERNÁNDEZ ,  Carlos CASADO MONTERO

IPC: B64D41/00 ,  B60L3/00 ,  B60L50/00 ,  F02C7/26 ,  H02J3/00

CPC classification number: B64D41/00 ,  B60L3/0092 ,  B60L50/00 ,  F02C7/26 ,  H02J3/0073 ,  B60L2200/10 ,  F05D2220/76 ,  F05D2260/85

Abstract: An auxiliary power generator system for an aircraft including an auxiliary power unit (APU) with dual and fully redundant starter and electrical power generation systems that connects independently to a normal electric network or an emergency electric network of an aircraft. A method for supplying electric power to an aircraft by means of the system.

公开(公告)号：US12006022B2

公开(公告)日：2024-06-11

申请号：US17526386

申请日：2021-11-15

Applicant: Airbus Operations S.L.U.

Inventor： Mario Linares Villegas ,  Silvia Garcia Toran

IPC: B64C1/26 ,  B64C1/06 ,  B64C9/02

CPC classification number: B64C1/26 ,  B64C1/0685 ,  B64C9/02

Abstract: An aircraft empennage, comprising a rear fuselage section, a trimmable horizontal tail plane comprising a first and a second lateral torsion box), each comprising a front spar and a rear spar, a front fitting and a rear fitting, an actuator acting on the front fitting for a rotation of the trimmable horizontal tail plane around a hinge axis passing through the rear fitting, the front fitting comprising a first and a second front fitting units being joined to the front spars of the lateral torsion boxes, and the actuator comprising first and a second actuator units, each acting on the first front fitting unit and the second front fitting unit respectively.

公开(公告)号：US11964758B2

公开(公告)日：2024-04-23

申请号：US17856567

申请日：2022-07-01

Applicant: AIRBUS OPERATIONS, S.L.U.

Inventor： Álvaro Jara Rodelgo ,  Alfonso Parra Rubio ,  Pablo Vázquez Sánchez ,  Esteban Martino González

IPC: B64C3/48 ,  B64C3/46 ,  B64C3/50

CPC classification number: B64C3/48 ,  B64C3/46 ,  B64C3/50

Abstract: An airfoil of an aerodynamic surface including: a control surface having an upper surface and a lower surface, and an actuator configured to elevate or lower the control surface, wherein at least a portion of one of the upper surface and the lower surface of the control surface is auxetic with a negative Poisson ratio, and the other of the upper surface and the lower surface of the control surface includes a material with a higher Poisson ratio.

公开(公告)号：US20230347607A1

公开(公告)日：2023-11-02

申请号：US18307263

申请日：2023-04-26

Applicant: Airbus Operations S.L.U.

Inventor： Matilde DE LA MOTA MENDIOLA ,  Jesús Javier VÁZQUEZ CASTRO ,  Asunción BUTRAGUEÑO MARTÍNEZ ,  Jorge BALLESTERO MÉNDEZ

IPC: B29D22/00

CPC classification number: B29D22/003

Abstract: A method for manufacturing a vessel configured for housing a fluid within, the method including: providing at least two at least partially cured fiber reinforced polymer (FRP) structures with complementary shapes configured for matching with each other such that an interior volume is defined when the at least partially cured FRP structures are coupled to each other; coupling the at least partially cured FRP structures to each other such that the interior volume is defined; winding at least one layer of FRP material onto at least a portion of the at least partially cured FRP structures once coupled to each other; and applying a curing cycle to cure the resulting assembly.

公开(公告)号：US20230194185A1

公开(公告)日：2023-06-22

申请号：US18081174

申请日：2022-12-14

Applicant: Airbus Operations S.L.U.

Inventor： Juan Tomás PRIETO PADILLA ,  Diego BARRÓN VEGA

IPC: F28D9/00 ,  F28D9/02 ,  F28D21/00

CPC classification number: F28D9/0062 ,  F28D9/02 ,  F28D21/00 ,  F28D2021/0021

Abstract: An aircraft heat exchanger arranged longitudinally and including a casing with an inner chamber configured so that coolant flows longitudinally from an inlet to an outlet, a plurality of laterally spaced longitudinally extending inner chamber plates, and a plurality of channels defined between contiguous plates. Each plate includes a leading edge oriented towards the inlet and configured to divert coolant towards the channels. A plurality of the plates include an inner hollow area configured to conduct a flow of hot bleed air therethrough. Leading edges of a first group of plates are arranged in a stepped pattern. A gap defined between the first group of plates and a first casing lateral wall establishes a fluid coolant communication through the first group of plates between the casing inlet and outlet. The lateral distance between each leading edge of the first group of plates and the first lateral wall decreases longitudinally.

公开(公告)号：US11619456B2

公开(公告)日：2023-04-04

申请号：US16830425

申请日：2020-03-26

Applicant: Airbus Operations, S.L.U.

Inventor： Brice Lenoir

IPC: F28F1/14 ,  B64D33/08 ,  F02C7/14 ,  F02C9/18

Abstract: A duct for a bleed system of an aircraft, wherein the duct extends from an inlet section to an outlet section along a longitudinal axis, and wherein the duct comprises a continuous piece arranged on and protruding from the internal wall of the duct. The duct is subject to temperature gradients in order to reduce the temperature of the warmest airflow closer to the inner wall rather than rapidly mix the airflow.