公开(公告)号：US11167854B2

公开(公告)日：2021-11-09

申请号：US15997005

申请日：2018-06-04

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Carlos Casado-Montero ,  Alberto Molina Parga

IPC: B64D13/08 ,  B64D33/02 ,  B64D41/00 ,  B64D13/06

Abstract: The invention relates to an aircraft incorporating an enhanced power unit for generating electric, pneumatic and/or hydraulic power for the aircraft during all stages of the aircraft operation. The power unit (1) comprises: a heat engine (14) with a drive shaft (2) and a combustion gases exhaust (7). The power unit (1) also includes a Rankine cycle system (12) for recovering thermal energy from a heat source of the power unit (1) for the assistance of the heat engine (14). The heat source for the Rankine cycle system can be taken from the exhaust gases of the heat engine, from the oil coolant circuit of the heat engine or from the output of a compressor driven by the heat engine. Preferably, the aircraft cabin air is reused as a source of oxygen for the combustion. The invention reduces bleed air extraction from the aircraft main engines thereby reducing fuel consumption.

公开(公告)号：US11131243B2

公开(公告)日：2021-09-28

申请号：US16281799

申请日：2019-02-21

Applicant: Airbus Operations S.L.

Inventor： Esteban Martino-Gonzalez ,  Iker Velez De Mendizabal Alonso ,  Vasilis Votsios ,  Guillermo Nicolas Gutierrez ,  Diego Sanchez Franco ,  David Matesanz Hidalgo ,  Jose Angel Hernanz-Manrique

IPC: F02C7/042 ,  B64D41/00 ,  B64D13/00 ,  B64C1/14 ,  B64D33/02 ,  B64C1/00

Abstract: An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.

公开(公告)号：US20210245889A1

公开(公告)日：2021-08-12

申请号：US17175003

申请日：2021-02-12

Applicant: Airbus Operations S.L.

Inventor： Alberto MARTINEZ SANCHO

IPC: B64D31/14 ,  B64F5/40

Abstract: A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.

公开(公告)号：US11052996B2

公开(公告)日：2021-07-06

申请号：US15872460

申请日：2018-01-16

Applicant: Airbus Operations S.L.

Inventor： Carlos García Nieto ,  Iker Vélez De Mendizábal Alonso ,  Soledad Crespo Peña ,  Enrique Guinaldo Fernández ,  Jesús Javier Vázquez Castro ,  Álvaro Torres Salas

IPC: B64C21/08 ,  B64C23/06 ,  B64C21/10

Abstract: A lifting device including: a movable discontinuity (1) located in a surface of the lifting device, the movable discontinuity (1) being movable between: an active position in which the movable discontinuity (1) acts as vortex generator, and a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface, a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface including openings (3) in its surface spanwise distant from each other in communication with the conduit (2), the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.

公开(公告)号：US20210138713A1

公开(公告)日：2021-05-13

申请号：US17097667

申请日：2020-11-13

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Salvador ROMERO ESTEBAN ,  Augusto PEREZ-PASTOR ,  Melania SANCHEZ PEREZ ,  Katia FERNANDEZ HORCAJO

IPC: B29C53/04 ,  B29C53/84

Abstract: A device for forming a composite laminate (10) for obtaining a Z-shaped profile (1) including: a grip module (5) comprising two plates (6) configured to enclose and grip between the two plates (6) a first portion of the composite laminate (10) that will form a first flange (3), and a feed module (7) comprising two plates (8) configured to enclose between the two plates (8) a second portion of the composite laminate (10), wherein the feed module (7) is configured to heat the portion of the composite laminate (10) located between its two plates (8) and to be movable with respect to the grip module (5) parallel to the plane of the web (2) of the composite profile (1) once formed to a second position in which the two plates (8) enclose the portion of the composite laminate (10) that will form a second flange (4).

公开(公告)号：US10961907B2

公开(公告)日：2021-03-30

申请号：US16018593

申请日：2018-06-26

Applicant: Airbus Operations, S.L.

Inventor： Marta Castillo De Alvear ,  Juan Tomas Prieto Padilla

IPC: B64D13/08 ,  F02C6/08 ,  F02C7/14 ,  B64D13/02 ,  B64D15/04 ,  F02K3/06 ,  F02K3/115 ,  B64D29/02 ,  F02C7/18 ,  F02C9/18 ,  B64D13/06 ,  F28D21/00 ,  B64D33/02

Abstract: An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.

公开(公告)号：US20210053669A1

公开(公告)日：2021-02-25

申请号：US16999198

申请日：2020-08-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Raul OLMO MORA ,  Tamara BLANCO VARELA

IPC: B64C1/40 ,  B32B5/02 ,  B29C70/22 ,  G10K11/168

Abstract: A sound wave absorbing laminate composite material structure for an aircraft including stacked plies of a hybrid composite material, wherein each of the hybrid composite material plies includes first polymer material tows parallel to a warp direction, second polymer material tows parallel to a weft direction, and sound absorbent material tows parallel to the warp direction, wherein the first and second polymer material tows carbon or glass fiber reinforcing polymer.

公开(公告)号：US10906631B2

公开(公告)日：2021-02-02

申请号：US15872619

申请日：2018-01-16

Applicant: Airbus Operations S.L.

Inventor： Carlos García Nieto ,  Iker Vélez De Mendizábal Alonso ,  Soledad Crespo Peña ,  Enrique Guinaldo Fernández ,  Jesús Javier Vázquez Castro ,  Álvaro Torres Salas

IPC: B64C23/06 ,  B64C5/10 ,  B64C9/18 ,  B64C5/02

Abstract: A lifting surface comprising a movable discontinuity located in the surface of the lifting surface. The movable discontinuity is movable between an active position in which the movable discontinuity acts as vortex generator, and a passive position in which the movable discontinuity is integrated into the surface of the lifting surface without acting as vortex generator. The lifting surface may be in an elevator, the elevator being rotatable around a hinge line with respect to the rest of the lifting surface. A bar is rigidly joined to the elevator. The bar, the elevator and the movable discontinuity are configured such that when the elevator rotates with respect to the rest of the lifting surface, the bar moves the movable discontinuity that departs from the surface of the lifting surface, acting as a vortex generator.

公开(公告)号：US10899091B2

公开(公告)日：2021-01-26

申请号：US16128935

申请日：2018-09-12

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Iker Velez De Mendizabal Alonso ,  David Apellaniz De La Fuente ,  Esteban Martino-Gonzalez-Aranjuez

IPC: B29C70/54 ,  B29C33/48 ,  B29D99/00 ,  B29D24/00 ,  B29C70/30 ,  B29K307/04 ,  B29L7/00

Abstract: A modular mold for producing a panel including a panel of fiber reinforced material. The panel is configured to form hollow cells having an undulated trapezoidal cross-section. The mold includes at least three molding bars for forming each hollow cell. One of the molding bars has a trapezoidal cross shape. The other two molding bars have a triangular cross shape. The trapezoidal molding bar is located between the two triangular molding bars. The three molding bars when put together its cross-section forms the shape of the trapezoidal cross-section of the hollow cell.

公开(公告)号：US20210001991A1

公开(公告)日：2021-01-07

申请号：US16916559

申请日：2020-06-30

Applicant: Airbus Operations S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Juan Tomas PRIETO PADILLA

IPC: B64D13/02 ,  B64D13/06

Abstract: An air management system with a set of compressed air sources for supplying pressurized air to air consumer equipment. In particular, either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.