公开(公告)号：US10773790B2

公开(公告)日：2020-09-15

申请号：US15843203

申请日：2017-12-15

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Edouard Menard ,  Esteban Martino González ,  Fernando Iniesta Lozano

IPC: B64C5/06 ,  B64C1/12 ,  B64C1/00 ,  B64D45/00

Abstract: An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material layer is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.

公开(公告)号：US20200231270A1

公开(公告)日：2020-07-23

申请号：US16744342

申请日：2020-01-16

Applicant: Airbus Operations, S.L.

Inventor： Robert KOBIERECKI ,  Miguel Ángel MENDEZ RODRÍGUEZ ,  Juan Antonio SÁNCHEZ RUIZ ,  Alberto BALSA-GONZALEZ

IPC: B64C9/00 ,  B29C65/60 ,  B29L31/30

Abstract: A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.

公开(公告)号：US10549836B2

公开(公告)日：2020-02-04

申请号：US15444498

申请日：2017-02-28

Applicant: Airbus Operations, S.L.

Inventor： Felipe Abellán Alzallu ,  Alberto Ramos Guerrero ,  Adolfo Ávila Gutierrez ,  Juan Carlos Monje Martin

IPC: B64C1/06

Abstract: A harness routing electrically connects a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section includes a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream from the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point.

公开(公告)号：US10549492B2

公开(公告)日：2020-02-04

申请号：US14725626

申请日：2015-05-29

Applicant: Airbus Operations, S.L.

Inventor： Gabriel Cruzado Parla ,  Fernando Munoz Ajenjo ,  Jose Cuenca Rincon ,  Maria Mora Medias

IPC: B29C33/68 ,  B29C70/44 ,  B29K105/08 ,  B29K307/04 ,  B29L31/30

Abstract: The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.

公开(公告)号：US10543928B2

公开(公告)日：2020-01-28

申请号：US15349180

申请日：2016-11-11

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Salvatore Demelas

IPC: B64D33/00 ,  B64D31/00

Abstract: An electric power distribution system for an aircraft is provided, which includes an engine gearbox, a power distribution center, two or more three-phase synchronous electric power generators, a neutral current transformer per generator, a single set of power feeder wires, and a single generator control unit (GCU). The generators are connected in parallel with each other, and connected with the power distribution center by the same set of power feeder wires. The GCU is electrically coupled with each generator to feed the generator with an excitation field current, and with each neutral current transformer to sense an instantaneous neutral-current value. The GCU is adapted to perform a generator voltage regulation loop based on a desired voltage value and the at least two sensed instantaneous neutral-current values by individually modifying the excitation field current of each generator.

公开(公告)号：US20200010218A1

公开(公告)日：2020-01-09

申请号：US16502436

申请日：2019-07-03

Applicant: Airbus Operations, S.L.

Inventor： Francisco Javier HONORATO RUIZ ,  Jesús Javier VÁZQUEZ CASTRO ,  Enrique GUINALDO FERNÁNDEZ ,  Carlos GARCÍA NIETO ,  Iker VÉLEZ DE MENDIZÁBAL ALONSO

IPC: B64F5/10 ,  B64C3/18

Abstract: A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.

公开(公告)号：US20190386474A1

公开(公告)日：2019-12-19

申请号：US16440165

申请日：2019-06-13

Applicant: AIRBUS OPERATIONS (S.A.S.) ,  AIRBUS OPERATIONS S.L. ,  AIRBUS OPERATIONS GMBH

Inventor： Alain RODEGHIERO ,  Jose SANCHEZ-GOMEZ ,  Tamara BLANCO VARELA ,  Cristobal Federico BRITO MAUR

IPC: H02G3/30 ,  H05K3/12 ,  H05K3/10 ,  H05K1/09 ,  H02G1/06 ,  B64D47/00 ,  B64C1/14

Abstract: A method for printed cable installation in a harness system of an aircraft. The method includes: printing at least a first conductive trace comprising conductive particles to a surface of an aircraft with a printing technology; printing at least second conductive trace comprising conductive particles to the surface of an aircraft with the printing technology; sintering the first and the second conductive traces by a laser, and interposing an insulating film between the first and the second conductive traces. For a trace length less than 5 meters, the first and second conductive traces provide the electromagnetic compatibility of a twisted pair of wires when printed with a guard trace.

公开(公告)号：US10472073B2

公开(公告)日：2019-11-12

申请号：US15395425

申请日：2016-12-30

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Carlos Casado Montero

IPC: B64D13/08 ,  B64D13/06

Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.

公开(公告)号：US10443623B2

公开(公告)日：2019-10-15

申请号：US15458688

申请日：2017-03-14

Applicant: AIRBUS OPERATIONS S.L. ,  Airbus Operations GmbH

Inventor： Antón Méndez Díaz ,  Javier Fraile Martin ,  Neus Busquets More ,  Jan Barkowsky

IPC: F04D29/58 ,  B64D15/04 ,  F04D27/00 ,  F04D29/54 ,  F04D29/56 ,  B64D13/08 ,  F02C6/08 ,  F02C9/18 ,  B64D13/06

Abstract: An engine bleed air system of an aircraft, comprising a heat exchanger which comprises a rectangular core with a rectangular outlet section, a cylindrical outlet duct and a transition area between the rectangular outlet section of the rectangular core and the cylindrical outlet duct, and at least a downstream system, further comprising a flow deflector located at least in the cylindrical outlet duct, such that the outlet flow characteristics homogeneity are improved and a particular flow deflection and distribution of the outlet flow is achieved, avoiding the damage of the at least one downstream system. The invention also provides a method for homogenizing the temperature of the outlet flow of a heat exchanger outlet in an engine bleed air system of an aircraft.

公开(公告)号：US20190264610A1

公开(公告)日：2019-08-29

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

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.