公开(公告)号：US11542028B2

公开(公告)日：2023-01-03

申请号：US16565766

申请日：2019-09-10

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Juan Manuel Canalejo Bautista

IPC: B64D33/02 ,  F02C7/052

Abstract: An air intake including an air duct inside an aircraft, an inlet at one end of the air duct, a flap door and driving mechanism that moves the flap door between closed and open positions. The flap door includes a barrier filter configured to filter an incoming airflow into the air duct, and wherein the driving mechanism is configured to pivot the flap door about a first end of the door.

公开(公告)号：US11541983B2

公开(公告)日：2023-01-03

申请号：US16442688

申请日：2019-06-17

Applicant: Airbus Operations S.L.

Inventor： Esteban Martino-Gonzalez ,  Alberto Arana Hidalgo ,  Melania Sanchez Perez ,  Carlos Garcia Nieto ,  Jesus Javier Vazquez Castro ,  Edouard Menard ,  Fernando Iniesta Lozano ,  Maria Almudena Canas Rios

IPC: B64C1/26 ,  B64F5/10

Abstract: A method for manufacturing a composite assembly with a continuous skin for a rear end of an aircraft by obtaining an upper part of the rear end by composite tooling. The upper part comprises a multi-spar vertical tail plane. The spars of the vertical tail plane comprise widening roots that form an upper shell of the rear end and an upper skin. Furthermore, a lower part comprises a lower shell of the rear end including semi-complete frames and stringers and a lower skin. The upper and lower parts are assembled with a joining procedure. The upper and lower skins are joined to obtain the composite assembly with the continuous skin.

公开(公告)号：US11518067B2

公开(公告)日：2022-12-06

申请号：US17129057

申请日：2020-12-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Pablo Cebolla Garrofe

IPC: B29B11/00 ,  B29B11/06 ,  B29K307/04

Abstract: A method for forming fiber composite preforms, the preform (1) include a web (2), a flange (3) and a bent part (2.1), and the method includes: laying-up a laminate (4) onto a tooling (5), the laminate (4) comprising lateral and transverse edges (4.1, 4.2) and the tooling (5) comprising a male part (7) comprising a surface (7.1) and a lateral wall (7.2), the web (2) being configured to be located over the surface (7.1) of the male part (7) and the flange (3) being configured to be located over the lateral wall (7.2) of the male part (7); forming the preform (1) over the male part (7); clamping the lateral edges (4.2) of the laminate (4) to the tooling (5) such that the web (2) and the flange (3) of the laid-up laminate (4) are kept under tensional loads, and bending a longitudinal portion of the male part (7).

公开(公告)号：US11440634B2

公开(公告)日：2022-09-13

申请号：US16521057

申请日：2019-07-24

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Elena Arevalo Rodriguez ,  Antonio Torres Esteban

IPC: B64C1/12 ,  B64C1/06 ,  B64F5/10 ,  B29L31/30 ,  B64C1/00

Abstract: A frame (1) for fuselage shells of an aircraft, the fuselage comprising a skin (3) and stringers (4), the frame (1) including: a plurality of sections (5), the sections (5) being separated by intermediate gaps corresponding to the position of the stringers (4) in the fuselage, each section (5) having a multi-cell configuration constituted by several modular elements (6) of composite material arranged in longitudinal direction, and a continuous inner cap (7) on top of the sections (5) and the intermediate gaps.

公开(公告)号：US11408338B2

公开(公告)日：2022-08-09

申请号：US16814506

申请日：2020-03-10

Applicant: Airbus SAS ,  Airbus Operations SAS ,  Airbus Operations, S.L.

Inventor： Bruno Medda ,  Esteban Martino-Gonzalez ,  Thomas Stevens ,  Julien Cayssials ,  Juan Tomas Prieto Padilla ,  Adeline Soulie ,  Didier Poirier ,  Pierre-Alain Pinault ,  Diego Barron Vega

IPC: F02C6/08 ,  B64D15/04 ,  F02C7/047 ,  F02C7/10 ,  B64D33/02

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

公开(公告)号：US11377204B2

公开(公告)日：2022-07-05

申请号：US16897611

申请日：2020-06-10

Applicant: Airbus Operations S.L.

Inventor： Alberto Arana Hidalgo

IPC: B64C23/06 ,  B64D41/00 ,  H01F7/06 ,  H01F7/20

Abstract: A retractable vortex generator system for an aircraft. The system comprises a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing the boundary layer of an air current, and driving means configured for rotating the plate between a first and a second position. In the first position at least part of the contour of the plate protrudes through the slot, and in the second position the plate is retracted within the slot.

公开(公告)号：US20220161940A1

公开(公告)日：2022-05-26

申请号：US17526120

申请日：2021-11-15

Applicant: Airbus Operations S.L.

Inventor： Pedro Manuel MARTIN CANDELARIO ,  Lucas GRANJA PAREJO ,  Carlos CASADO-MONTERO

IPC: F02K1/34 ,  B64D41/00 ,  G10K11/162

Abstract: An exhaust muffler for an APU of an aircraft, including an exhaust gases inlet, an exhaust gases outlet, a peripheral wall configured to guide a flow of exhaust gases between the inlet and the outlet. The peripheral wall includes at least one vacuum chamber to provide thermal insulation.

公开(公告)号：US11319047B2

公开(公告)日：2022-05-03

申请号：US15957289

申请日：2018-04-19

Applicant: Airbus Operations, S.L.

Inventor： Iker Vélez De Mendizábal Alonso ,  Esteban Martino González ,  David Apellaniz De La Fuente ,  Alfonso Parra Rubio ,  Elena Moya Sanz

IPC: B64D45/00 ,  B64D33/02 ,  B33Y10/00 ,  B33Y80/00 ,  B21D5/16 ,  B29K101/12 ,  B29L31/08 ,  B29L31/30 ,  B64C1/12 ,  F01D5/14 ,  A43B1/00 ,  B29D99/00 ,  F01D21/14 ,  B64C11/26 ,  F01D11/00 ,  B31D3/02 ,  A43B13/02 ,  A43B13/14 ,  B29C53/04 ,  B32B3/12 ,  B32B15/01 ,  B32B27/08 ,  B64C3/26 ,  B64C11/20 ,  B64C1/00 ,  F01D5/28 ,  B64C27/473 ,  F01D21/04

Abstract: A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

公开(公告)号：US20220032561A1

公开(公告)日：2022-02-03

申请号：US17504652

申请日：2021-10-19

Applicant: Airbus Defence and Space GmbH ,  Airbus Operations, S.L.

Inventor： Katharina Schlegel ,  Alois Friedberger ,  David Lopez-Bravo

IPC: B29C70/38 ,  B29C70/34 ,  B29C70/50

Abstract: A fiber composite laying method for producing a fiber composite scrim for forming a fiber composite component. The method includes supplying a reinforcement fiber band to a laying head, laying and compacting the supplied reinforcement fiber band on a laying surface at an average compaction pressure by a compaction roller, and detecting a local compaction pressure on the laid reinforcement fiber band by pressure sensors on the compaction roller.

公开(公告)号：US11215118B2

公开(公告)日：2022-01-04

申请号：US16712232

申请日：2019-12-12

Applicant: Airbus (S.A.S.) ,  Airbus Operations (S.A.S.) ,  Airbus Operations, S.L.

Inventor： Bruno Medda ,  Thomas Stevens ,  Julien Cayssials ,  Adeline Soulie ,  Didier Poirier ,  Pierre-Alain Pinault ,  Esteban Martino González ,  Juan Tomas Prieto Padilla ,  Diego Barron Vega

IPC: F02C7/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  F02C7/047 ,  F02C6/08 ,  F02C7/14 ,  B64D13/06

Abstract: An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.