公开(公告)号：US20200291869A1

公开(公告)日：2020-09-17

申请号：US16814494

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: F02C9/18 ,  F02C7/10

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.

公开(公告)号：US20200079519A1

公开(公告)日：2020-03-12

申请号：US16565766

申请日：2019-09-10

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Juan Manuel CANALEJO BAUTISTA

IPC: B64D33/02

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：US20190389601A1

公开(公告)日：2019-12-26

申请号：US16444669

申请日：2019-06-18

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Pedro VALERA RODRIGUEZ ,  Alejandro ROSIQUE GOMEZ

IPC: B64F5/60 ,  B64C1/12 ,  H04N5/74 ,  B64C1/06 ,  G06K9/46

Abstract: A projector to project a pattern on a surface of an aircraft. The projector includes software configured to read a pattern, and a projector configured to project the read pattern onto the surface of the aircraft. The pattern is a map of structural images corresponding to the structural components mounted behind the skin of the aircraft, such as a fuselage, and frame references corresponding to predetermined visible points on the skin of the aircraft. The frame references are aligned with the predetermined visible points of the fuselage to match the pattern with the aircraft and the structural items are identified based on the structural references.

公开(公告)号：US20190382137A1

公开(公告)日：2019-12-19

申请号：US16441448

申请日：2019-06-14

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: B64F5/10 ,  B64C1/06

Abstract: A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.

公开(公告)号：US10481040B2

公开(公告)日：2019-11-19

申请号：US15215768

申请日：2016-07-21

Applicant: Airbus Operations, S.L.

Inventor： José Maria Diaz Parrilla ,  Álvaro Jara Rodelgo ,  Miguel Ángel Gallego Lorenzo ,  José Ángel Hernanz Manrique

IPC: G01M9/04 ,  B64F5/60

Abstract: A boundary layer suction system adapted to a surface exposed to the circulation of a fluid. The system comprises a portion of the surface, a bifurcation element for bifurcating a mass of fluid flowing along the front face of the surface, comprising an airfoil-shaped cross-section such that the fluid is bifurcated into a first and a second flow, a slot located on the portion of the surface and downstream of the leading edge of the bifurcation element, the slot communicating the front and the rear faces of the portion of the surface, and an arrangement to provide a pressure difference between the front and the rear faces of the surface around the slot, such that a suction of the boundary layer is performed through the slot by the pressure difference.

公开(公告)号：US10408719B2

公开(公告)日：2019-09-10

申请号：US15804053

申请日：2017-11-06

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Ricardo Pinillos Martínez ,  Augusto Pérez Pastor ,  Gema Lorena Fernández Artalejo

IPC: G01N3/08 ,  G01N19/04 ,  G01N33/00

Abstract: A system for testing bonded joints that comprises a swing tool, an actuator, pressure measuring device and a first fixing arrangement. The actuator of the system is configured to apply a compression force or a traction force on the swing tool in order to separate two elements, and the pressure measuring device is configured to measure the force applied on the swing tool. A method for testing bonded joints using the system is also provided.

公开(公告)号：US10399659B2

公开(公告)日：2019-09-03

申请号：US14977121

申请日：2015-12-21

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

Inventor： Zengli Han ,  Haifeng Chen ,  Ming Luo ,  Angel Postigo-Rodriguez ,  Daniel De-La-Sen-Perez ,  Laure Partouche

IPC: B64C1/14 ,  E06B3/04 ,  E05C3/12 ,  B64C3/34

Abstract: The present invention relates to a door for closing an opening in a structure, including: a body arranged to be capable of abutting against a first side of the opening; at least one clamping member configured to be capable of abutting against an opposite second side of the opening; and a fastener arranged to fasten or release the clamping member relative to the body. The clamping member is moveable relative to the body between a first position where the clamping member abuts against the second side of the opening so as to clamp the structure between the body and the clamping member and a second position where the clamping member allows the door to be opened. The present invention further relates to an aircraft including the above door.

公开(公告)号：US20190161211A1

公开(公告)日：2019-05-30

申请号：US16197719

申请日：2018-11-21

Applicant: Airbus Operations, S.L.

Inventor： Alberto ARANA HIDALGO ,  José Luis MARTÍNEZ MUÑOZ

IPC: B64F5/50 ,  B64D27/02 ,  B64D27/26 ,  B64D41/00

Abstract: An aircraft with a system for rearward mounting and dismounting an engine, the engine being placed inside the rear part of the aircraft when mounted. The system for rearward mounting and dismounting the engine comprises a first removable attachment device arranged to attach the engine to the fuselage in the rear part of the aircraft, internal supports fixed in the rear part of the aircraft, at least two longitudinal detachable rails, to be placed on the internal supports and under the engine, and a slider to attach to the engine via a second removable attachment device, to be placed on the longitudinal detachable rails.

公开(公告)号：US20190150290A1

公开(公告)日：2019-05-16

申请号：US16190636

申请日：2018-11-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Alvaro JARA RODELGO ,  Alvaro TORRES SALAS ,  Elena MOYA SANZ ,  Paloma LLORENTE GARCIA

IPC: H05K3/00 ,  H05K1/02 ,  H05K1/03 ,  H05K1/18 ,  G01B5/00

Abstract: A 3D printed drilling template (20, 30a, 30b, 30c) including: a rigid framework able to be manipulated by an operator or an automaton, and a set of traversing (22, 32a, 32b, 32c, 33c) orifices in the framework and arranged to guide the drilling of holes into a structure on which the drilling template is mounted, wherein the drilling template (20, 30a, 30b, 30c) is designed or revised on an ad-hoc basis and manufactured by 3D printing and using a 3D printing material based on a polymer material mixed with powdered graphene.

公开(公告)号：US20190145550A1

公开(公告)日：2019-05-16

申请号：US16190732

申请日：2018-11-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Francisco Javier HONORATO RUIZ ,  Diego SANCHEZ FRANCO ,  Luis RODRIGUEZ URBINA ,  Enrique GUINALDO FERNANDEZ ,  Carlos GARCIA NIETO

IPC: F16L3/123 ,  H02G3/00

CPC classification number: F16L3/123 ,  B29C65/5014 ,  B29C65/5042 ,  B29C65/561 ,  B29C65/562 ,  B29C66/112 ,  B29C66/114 ,  B29C66/474 ,  B29C66/532 ,  B29C66/721 ,  B29C66/72143 ,  B29C66/727 ,  B29C66/73751 ,  B29C66/7392 ,  B29C70/74 ,  B29L2031/3076 ,  B29L2031/737 ,  F16B2/10 ,  F16B5/0685 ,  F16B7/0433 ,  F16B9/02 ,  H02G3/26

Abstract: A composite structure (1) for an aircraft, having at least one insert (2) for receiving attachment devices, each insert (2) includes a core (3) having a major dimension and containing at least one through-hole (4), and a composite strip arrangement formed by a first section (5) surrounding the core (3) and attached to said core (3) by an adhesive polymeric layer, and a second section (6) including at least one free end (6a). The first (5) and the second portion (6) of the composite strip arrangement are disposed over a first surface (1a) of the composite structure (1), such that the major dimension of the core (3) is positioned transversal to said first surface (1 a). The at least one insert (2) is co-cured with the composite structure (1).