公开(公告)号：US20190023372A1

公开(公告)日：2019-01-24

申请号：US16037269

申请日：2018-07-17

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

Inventor： Rodolphe Trouve ,  Jean-Claude Lacombe ,  Julien Rodes ,  Thomas Schutz

IPC: B64C3/14 ,  B64C3/26

Abstract: An aerodynamic profile including a skin defining the outer surface of the aerodynamic profile, a leading edge, a trailing edge and a central portion representing at least 50% of the chord of the profile. The profile includes a hollow core of composite material reinforced with a textile having unidirectional fibers. The hollow core has, in cross section, an oblong shape that is rounded, in particular at each of its ends. The skin bears against the hollow core over the length of the central portion of the aerodynamic profile, both on the pressure side and on the suction side of the profile. The reinforcement with a textile having unidirectional fibers permits an ideal orientation of reinforcing fibers in order to optimize mechanical properties in certain directions. The shape of the hollow core, elongate along the chord of the profile and rounded, lends it great resistance to deformation.

公开(公告)号：US20190003420A1

公开(公告)日：2019-01-03

申请号：US16001331

申请日：2018-06-06

Applicant: Airbus Operations S.A.S.

Inventor： Olivier Pautis

IPC: F02K1/72 ,  F02K1/76

Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.

公开(公告)号：US20180372024A1

公开(公告)日：2018-12-27

申请号：US16007006

申请日：2018-06-13

Applicant: Airbus Operations S.A.S.

Inventor： Olivier Pautis ,  Lionel Czapla

IPC: F02K1/70 ,  F02K1/76

CPC classification number: F02K1/70 ,  F02K1/72 ,  F02K1/763

Abstract: A thrust reverser system includes two thrust reversal cascades, of which the first cascade is entrained by an actuator, and which are configured to adopt a retracted position in which they are housed in a space located outside the duct. The action of the actuator brings about: rearward displacement of the first cascade in the direction of a nacelle opening; and during part of the rearward displacement of the second cascade, simultaneous pivoting of this second cascade under the action of a control lever, the interaction of which with a fixed guide rail forces the front end of the lever to move radially inwards while the lever is entrained rearwards by the second cascade.

公开(公告)号：US20180366982A1

公开(公告)日：2018-12-20

申请号：US16005322

申请日：2018-06-11

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

Inventor： Aymeric Plo ,  Xavier Alquier

IPC: H02J50/10 ,  G01D11/24

Abstract: A portable measuring system including an electronic acquisition device, at least one sensor linked to the acquisition device, and a power supply module. The power supply module includes at least one electric torus to be mounted on electrical wiring in order to generate a current by induction, and an electric power management device that delivers a voltage-stabilized current in order to power the acquisition device. An assembly includes an external data centralizer. Such a system or assembly is easy to install, has potentially unlimited autonomy, and is particularly well suited to use in an aircraft.

公开(公告)号：US20180343422A1

公开(公告)日：2018-11-29

申请号：US15978416

申请日：2018-05-14

Applicant: Airbus Operations S.A.S.

Inventor： Aurelien Rautureau ,  Frédéric Bertrand ,  Olivier Daffos

IPC: H04N7/18 ,  G01N29/44 ,  G01N27/90 ,  G06F3/14 ,  G02B27/01

Abstract: A non-destructive inspection device includes: a probe, a camera configured to film an area of the part inspected by the probe, a first display and a second display system configured to allow a display of at least one image filmed by the camera. This configuration makes it possible to remotely display the area of the part inspected by the probe.

公开(公告)号：US20180340795A1

公开(公告)日：2018-11-29

申请号：US15980991

申请日：2018-05-16

Applicant: Airbus Operations S.A.S. ,  Office National d'Etudes et de Recherches Aerospatiales (ONERA)

Inventor： Philippe Goupil ,  Martin Delporte ,  Cedric Seren ,  Georges Hardier ,  Guillaume Alcalay

IPC: G01C23/00 ,  B64D43/02 ,  G01C9/00 ,  G01C5/00

Abstract: A device for monitoring and estimating parameters relating to the flight of an aircraft includes an estimation module 4 for determining an estimation of the values of the parameters relating to the flight of the aircraft and for generating residues, a detection module for determining the statuses associated with each of said sensors C1, C2, . . . , CN and with a parameter P1 corresponding to the weight of the aircraft, a transmission module for transmitting the statuses associated with each of said sensors C1, C2, . . . , CN to a user device and, on the next iteration, to the estimation module.

公开(公告)号：US20180327104A1

公开(公告)日：2018-11-15

申请号：US15919970

申请日：2018-03-13

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

Inventor： Antoine Abele ,  Jean-Michel Rogero ,  Julien Guillemaut ,  Mathieu Belleville

IPC: B64D35/08 ,  B64D27/10 ,  B64D35/02 ,  F02C6/02 ,  F02C6/20

CPC classification number: B64D35/08 ,  B64D27/10 ,  B64D27/14 ,  B64D27/20 ,  B64D35/02 ,  B64D2027/026 ,  F01D13/003 ,  F02C6/02 ,  F02C6/206 ,  F02K3/04 ,  F02K3/12 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2260/84

Abstract: An aircraft propulsion assembly including a fan. It include a first engine and a second engine which are not coaxial and a mechanical energy transmission device configured to enable the fan to be conjointly rotated by the first engine and the second engine. This allows an aircraft propulsion assembly to be produced of which the fan may be positioned so as to ingest the boundary layer formed at the surface of a member of the aircraft equipped with the propulsion assembly, while allowing operating modes in the case of certain failures, and certification for commercial use of an aircraft equipped with such a propulsion assembly, to which the invention also relates.

公开(公告)号：US10118711B2

公开(公告)日：2018-11-06

申请号：US15359528

申请日：2016-11-22

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

Inventor： Cédric Consola ,  Olivier Blusson ,  Jean-Philippe Sabathier

IPC: B64D31/06

Abstract: The disclosure herein relates to a method of controlling the thrust of the jets of a multi-jet aircraft, during the aircraft takeoff phase, which successively comprises a first step of controlling the jets to a first thrust level, until the aircraft reaches a first predetermined speed, and a second step of controlling the jets to a second thrust level, less than the first thrust level, when the aircraft exhibits a speed greater than the first predetermined speed, the first predetermined speed being less than the minimum ground control speed of the aircraft when the jets are at the second thrust level.

公开(公告)号：US10113224B2

公开(公告)日：2018-10-30

申请号：US15294092

申请日：2016-10-14

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

Inventor： Cédric Poupon

IPC: C03C27/00 ,  C23C4/123 ,  C22C19/07 ,  C23C4/08 ,  C23C4/18 ,  C23C8/12 ,  C23C8/02 ,  C23C8/28 ,  C22F1/10

Abstract: An adjustment interface inserted between a first part made of nickel or made of nickel alloy or made of cobalt-chromium alloy in relative motion with a second part made of nickel or made of nickel alloy or made of cobalt-chromium alloy. The interface includes a first adjustment layer on one of the two parts and has a composition that makes it possible, with the friction with the other part, to create a glaze-type layer. A second adjustment layer is deposited on the second part for cooperation with the first layer to act as a catalyst for the oxide formed by friction with the first layer. The first glaze layer of the interface improves the sliding of the parts under friction. The catalyst function provided by the second layer makes it possible to stabilize the oxide formed by friction and to thus ensure a lubrication function over an extended high-temperature range.

公开(公告)号：US20180308369A1

公开(公告)日：2018-10-25

申请号：US15957329

申请日：2018-04-19

Applicant: Airbus Operations S.A.S.

Inventor： Jean-luc Robin

IPC: G08G5/00 ,  G08G5/04

CPC classification number: G08G5/0008 ,  G01S2205/005 ,  G05D1/104 ,  G08G5/0021 ,  G08G5/0078 ,  G08G5/0091 ,  G08G5/04 ,  G08G5/045

Abstract: A method for transmitting flight parameters from a leading aircraft (L) to at least one intruding aircraft (I), wherein, the transmission is effected by a collision avoidance system of TCAS type. The transponder of the leading aircraft (L) is configured to measure the spectrum of an interrogation signal received from the intruding aircraft (I) and to compare the power of the spectrum to a threshold power. If the power of the interrogation signal is greater than or equal to the threshold power, then the intruding aircraft (I) is eligible to receive flight parameters from the leading aircraft to be able to compute the position of the centres or the force of circulation of wake vortexes (14L, 15L) generated by the leading aircraft (L). The exchange of flight parameters from the leading aircraft only to eligible intruding aircraft makes it possible to not exceed the maximum automated communication bandwidth capacity.