公开(公告)号：US09708071B2

公开(公告)日：2017-07-18

申请号：US14137334

申请日：2013-12-20

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

Inventor： Thierry Surply ,  Cyril Bonnaud ,  David Grossein ,  Stéve Bedoin ,  Amadou AndréSylla ,  Guillaume Drochon ,  Marjorie Clottes

IPC: B64D27/26 ,  B64C7/02 ,  B64D29/02 ,  B64D33/04 ,  F01D25/14 ,  F02C7/12 ,  F02K1/82

CPC classification number: B64D27/26 ,  B64C7/02 ,  B64D29/02 ,  B64D33/04 ,  B64D2027/268 ,  F01D25/14 ,  F02C7/12 ,  F05D2220/327 ,  F05D2260/202 ,  Y02T50/675

Abstract: The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.

公开(公告)号：US20170191568A1

公开(公告)日：2017-07-06

申请号：US15378866

申请日：2016-12-14

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： David KASLIN

IPC: F16K1/20 ,  F16K1/16 ,  F16K31/00 ,  B64D41/00

CPC classification number: F16K1/2007 ,  B64D41/00 ,  F16K1/165 ,  F16K31/003 ,  H02K1/32 ,  H02K5/12 ,  H02K2205/09 ,  Y10T137/108 ,  Y10T137/7891 ,  Y10T137/7894

Abstract: An electric generator for an aircraft includes a sealed casing, a rotating shaft, and a ventilation device, which has at least one orifice configured to place a chamber positioned inside the rotating shaft in communication with the exterior of the sealed casing. For at least one orifice, an inertia sealing system is configured to occupy an open state when the speed of rotation of the rotating shaft is below a given threshold, in which state the sealing system is spaced from the orifice, and a closed state when the speed of rotation of the rotating shaft is above the given threshold, in which state the sealing system seals the orifice.

公开(公告)号：US20170171112A1

公开(公告)日：2017-06-15

申请号：US15376606

申请日：2016-12-12

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

Inventor： Jean-François SAINT-ETIENNE ,  Juan Lopez

IPC: H04L12/931 ,  H04L12/935 ,  H04L12/933 ,  H04L29/08 ,  H04L12/46

CPC classification number: H04L49/351 ,  H04L12/40006 ,  H04L12/4625 ,  H04L12/4641 ,  H04L49/15 ,  H04L49/30 ,  H04L67/12 ,  H04L2012/4028

Abstract: A subscriber of a deterministic Ethernet communication network using virtual links including a first receiver, a first transmitter, a first memory to record a configuration table relating to a set of virtual links that the subscriber can receive and/or retransmit. A processing unit is configured to implement at least one application, a reception function to receive data frames received by the first receiver, to accept the reception only of the frames corresponding to virtual links belonging to the set of virtual links and to transmit these frames to a sorting function to transmit the data frames received to the application and/or to a transmission function to dispatch the data frames received to the first transmitter while complying with Bandwidth Allocation Gap (BAG) constraints associated with the corresponding virtual links.

公开(公告)号：US20170166300A1

公开(公告)日：2017-06-15

申请号：US15374652

申请日：2016-12-09

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

Inventor： Christian Cros ,  Jérôme Phalippou ,  Christophe Mialhe ,  Jacques Peres

IPC: B64C25/16 ,  B64C25/20

CPC classification number: B64C25/16 ,  B64C25/20

Abstract: A system for the control of the door assemblies of a bay of a landing gear of an aircraft, that is retractile and is able to be deployed, the opening of the bay for the landing gear being able to be closed by a forward door assembly and an aft door assembly, comprises a coupling mechanism of the forward door assembly and the aft door assembly, that is configured such that the aft door assembly is not completely closed, but is ajar, as soon as the forward door assembly is opened during the deployment of the landing gear and the aft door assembly is completely closed at the complete closing of the forward door assembly when the landing gear is retracted.

公开(公告)号：US09673620B2

公开(公告)日：2017-06-06

申请号：US13864462

申请日：2013-04-17

Applicant: Airbus Operations GmbH ,  Airbus Operations S.A.S

Inventor： Martin Johannsen ,  Torben Schroeter ,  Lucien Prisse ,  Jerome Mavier ,  Martina Hinze

IPC: H02J1/00 ,  H02J4/00

CPC classification number: H02J1/00 ,  H02J4/00 ,  H02J2001/008 ,  Y10T307/25

Abstract: An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network.

公开(公告)号：US20170152024A1

公开(公告)日：2017-06-01

申请号：US15359146

申请日：2016-11-22

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

Inventor： Jérôme Colmagro

IPC: B64C21/04 ,  B64D27/26

CPC classification number: B64C21/04 ,  B64C3/28 ,  B64C21/025 ,  B64C2003/147 ,  B64D27/26 ,  B64D29/04 ,  F05D2240/90 ,  Y02T50/166

Abstract: A device including a profiled member conformed to constitute an edge portion of an aircraft aerodynamic profile. The device includes a blower chamber to be pressurized and an air ejector nozzle making it possible to provide fluidic communication between the blower chamber and an external surface of the profiled member, the profiled member, the blower chamber and the nozzle forming an assembly to be mounted in one piece on the aerodynamic profile to constitute a trailing edge thereof. The blower chamber and the nozzle are formed directly in the profiled member, the profiled member, the blower chamber and the air ejector nozzle being formed in one piece.

公开(公告)号：US09663219B2

公开(公告)日：2017-05-30

申请号：US14807014

申请日：2015-07-23

Applicant: Airbus Operations S.A.S.

Inventor： Mathieu Carton ,  Pierre Debusschere ,  David Chabe

IPC: B64C13/00 ,  B64D39/00 ,  G05D1/08 ,  G05D1/06

CPC classification number: B64C13/00 ,  B64D39/00 ,  G05D1/0607 ,  G05D1/0808

Abstract: The system comprises at least one lift generator element that is able to modify directly the lift of the aircraft and means for defining a deflection instruction upon actuation by a pilot of the aircraft of a control column of the aircraft generating a vertical load factor control value and applying it to an elevator and simultaneously defining a command instruction and applying it to the lift generator element to generate a direct lift.

公开(公告)号：US09657685B2

公开(公告)日：2017-05-23

申请号：US14269815

申请日：2014-05-05

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Guillaume Bulin ,  Armand Ruggeri

IPC: F02K1/30 ,  F02K1/09 ,  F02K1/15

CPC classification number: F02K1/30 ,  F02K1/09 ,  F02K1/15 ,  F05D2260/40 ,  F05D2260/57 ,  F05D2260/84 ,  F05D2260/902 ,  Y02T50/677

Abstract: A variable cross-section nozzle of an aircraft has at least two movable parts enabling modification of the cross-section of the nozzle. A control device for the nozzle includes a system for regulating the engine, the system being connected to a control element which drives at least one electric motor which creates the movement of the movable parts, including an electric motor for each movable part and two mechanical transmission systems for each movable part connected only to the same electric motor.

公开(公告)号：US20170106990A1

公开(公告)日：2017-04-20

申请号：US15292173

申请日：2016-10-13

Applicant: Airbus Operations S.A.S.

Inventor： Frederic Journade ,  Eric Bouchet ,  Gerard Coudouent ,  Bogdan Sina ,  Romain Terral ,  Sylvain Cros ,  Jerome Puech ,  Cyrielle Rogeron

IPC: B64D27/26 ,  B64C1/06

CPC classification number: B64D27/26 ,  B64C1/064 ,  B64D2027/264 ,  B64D2027/266

Abstract: An aircraft engine pylon includes two side panels and an upper stringer and a lower stringer assembled to form a strut assembly extending in a longitudinal direction (AX) corresponding to the direction in which the aircraft is moving and an internal reinforcement structure including a plurality of reinforcements. The pylon also includes a reinforcement zone on each side panel and a front housing to receive a main front centre reinforcement and a rear housing to receive a main rear centre reinforcement.

公开(公告)号：US09611039B2

公开(公告)日：2017-04-04

申请号：US14263376

申请日：2014-04-28

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Patrick Lieven ,  Romain Delahaye ,  Catalin Perju

IPC: B64D11/00 ,  B64D9/00 ,  B64C1/00 ,  B64C39/10

CPC classification number: B64D11/00 ,  B64C1/00 ,  B64C2001/0045 ,  B64C2039/105 ,  B64D9/00

Abstract: The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers.