公开(公告)号：US09932900B2

公开(公告)日：2018-04-03

申请号：US14530013

申请日：2014-10-31

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

Inventor： Yannick Sommerer ,  Stéphanie Jeanmougin

IPC: F02C7/18 ,  F02C7/24 ,  F01D25/12 ,  F02C7/32

CPC classification number: F02C7/18 ,  F01D25/12 ,  F02C7/24 ,  F02C7/32 ,  F05D2260/202 ,  Y02T50/676

Abstract: A thermal protection device for equipment positioned in an engine compartment of an aircraft turbomachine is disclosed. The device comprises at least one heat shield arranged at least partially between the equipment and a thermally radiative wall of the engine compartment exposed to a heating source. The heat shield comprises an air-channeling elements connected to a cooling air source and configured to direct cooling air toward the equipment.

公开(公告)号：US09920789B2

公开(公告)日：2018-03-20

申请号：US15466478

申请日：2017-03-22

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

Inventor： Camille Chaper ,  David Blain

IPC: F16C11/12 ,  F16D3/56

CPC classification number: F16C11/12 ,  F16D3/005 ,  F16D3/56 ,  Y10T403/32008 ,  Y10T403/453

Abstract: A universal joint includes a first band and a second band which are separated by a slot, are cylindrical and coaxial with one another with respect to a common axis, a first stiffener whose ends are joined to the first band, and a second stiffener whose ends are joined to the second band. A stem extends between the first stiffener and the second stiffener. A crown is around the stem. Four torsion bars exist, of which two extend between the crown and the first band and two extend between the crown and the second band.

公开(公告)号：US09868545B2

公开(公告)日：2018-01-16

申请号：US14573447

申请日：2014-12-17

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

Inventor： Wolfgang Brochard ,  Sébastien Alby ,  David Ewens

IPC: B64D45/00 ,  B64D27/26 ,  A62C3/08 ,  F02C7/25 ,  F02C7/20 ,  A62C2/06

CPC classification number: B64D45/00 ,  A62C2/065 ,  A62C3/08 ,  B64D27/26 ,  B64D2045/009 ,  F02C7/20 ,  F02C7/25 ,  F05D2300/702 ,  Y02T50/672

Abstract: A protective assembly and structural element for an aircraft comprising a portion of an attachment pylon primary structure is provided. The attachment pylon primary structure portion is at least partially covered by a protective assembly comprising a layer forming a firewall and a thermally insulating layer, the thermally insulating layer being located between the layer forming a firewall and the attachment pylon primary structure portion. The protective assembly is attached to the pylon primary structure by fasteners axially arranged in pairs, one of each pair extending through the protective assembly and the other of each pair extending through the pylon primary structure.

公开(公告)号：US09862497B2

公开(公告)日：2018-01-09

申请号：US14571772

申请日：2014-12-16

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

Inventor： David Ewens ,  Jonathan Blanc

IPC: B64D27/26 ,  B64D27/16 ,  B64F5/40 ,  B64D27/18

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/262 ,  B64D2027/264 ,  B64D2027/266 ,  B64F5/40 ,  Y10T29/49815

Abstract: In order to decrease the overall mass of an assembly for an aircraft, including an engine attachment pylon and an engine attachment, the pylon according to the disclosure herein has a primary structure forming a box section equipped with internal transverse stiffening ribs, one of which is produced in one piece with at least a part of the body of the engine attachment.

公开(公告)号：US09851022B2

公开(公告)日：2017-12-26

申请号：US14662758

申请日：2015-03-19

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

Inventor： Anne-Laure Neveu ,  Richard Brethes ,  Alexandre Maurel

IPC: B64C1/40 ,  F16L3/02 ,  F16L3/10

CPC classification number: F16L3/02 ,  B64C1/406 ,  F16L3/1058

Abstract: A mounting system for pipes, the mounting system including a mounting plate for being fixed onto a support, a pipe holder integral with the mounting plate and including a first supporting surface and a second supporting surface, each supporting surface being designed to accommodate a pipe and including a different shape from that of the other supporting surface, and adjustment structure designed to ensure a displacement of the pipe holder on the mounting plate along an adjustment direction and to ensure a blocking of the pipe holder on the mounting plate.

公开(公告)号：US20170361917A1

公开(公告)日：2017-12-21

申请号：US15618294

申请日：2017-06-09

Applicant: Airbus Operations S.A.S.

Inventor： Frédéric Sauvinet

IPC: B64C9/00 ,  B64C5/10 ,  B64C5/06 ,  B64C39/12 ,  B64C5/02

CPC classification number: B64C9/00 ,  B64C5/02 ,  B64C5/06 ,  B64C5/10 ,  B64C9/02 ,  B64C39/12

Abstract: An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

公开(公告)号：US09821918B2

公开(公告)日：2017-11-21

申请号：US14480016

申请日：2014-09-08

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

Inventor： Guillaume Bulin ,  Pierre Calvairac ,  Nicolas Lecointre ,  Paul-Emile Roux

IPC: B64D33/04 ,  F02K1/09 ,  F02K1/15 ,  B64D31/14 ,  B64D35/08

CPC classification number: B64D33/04 ,  B64D31/14 ,  B64D35/08 ,  B64D2221/00 ,  F02K1/09 ,  F02K1/15 ,  F05D2260/84 ,  Y02T50/677

Abstract: The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

公开(公告)号：US09815550B2

公开(公告)日：2017-11-14

申请号：US14865924

申请日：2015-09-25

Applicant: AIRBUS SAS ,  Airbus Operations S.A.S.

Inventor： Yann Nicolas ,  Philippe Tatry ,  Matthieu Bradier ,  Nicolas Sanz

IPC: B64C25/00 ,  B64C25/34 ,  H02P3/12 ,  B64C25/02 ,  B64C25/40 ,  B64C25/42

CPC classification number: B64C25/34 ,  B64C25/02 ,  B64C25/405 ,  B64C25/42 ,  H02P3/12 ,  Y02T50/823

Abstract: A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.

公开(公告)号：US09807670B2

公开(公告)日：2017-10-31

申请号：US13828378

申请日：2013-03-14

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

Inventor： Severine Vermande ,  Fabrice Vermande ,  Etienne Maynier

IPC: H04W40/20 ,  H04B7/185

CPC classification number: H04W40/20 ,  H04B7/18506

Abstract: In a communications network including aircraft in flight and at least one ground station, which constitute communication nodes of the network, data are transmitted from a source node to a destination node following a non-predetermined path through the network that includes at least one node which is a so-called intermediate aircraft. Before transmitting data from a transmitting node to at least one receiving node, it envisages a step of selecting the receiving node defining a portion of the path without knowledge of the next portion of the path.

公开(公告)号：US09789948B2

公开(公告)日：2017-10-17

申请号：US14448807

申请日：2014-07-31

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

Inventor： Yannick Marin ,  Emilie Luche

IPC: B64C1/12 ,  B64F5/10 ,  B64C1/06

CPC classification number: B64C1/12 ,  B64C1/061 ,  B64C1/068 ,  B64F5/10 ,  Y02P70/585 ,  Y10T29/4981 ,  Y10T29/49947

Abstract: A system with attachment clips designed to fix an attachment element of an aircraft fuselage frame onto a fuselage skin and/or to stiffeners fitted onto this fuselage skin is provided. The system includes tooling elements arranged alternately with the clips such that they connect to each other, in order to reduce the fabrication time and cost of an aircraft fuselage.