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.

公开(公告)号：US20180304986A1

公开(公告)日：2018-10-25

申请号：US15961295

申请日：2018-04-24

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

Inventor： Alain Porte ,  Jacques Lalane ,  Maud Lavieille

IPC: B64C1/40 ,  G10K11/168 ,  G10K11/172

CPC classification number: B64C1/40 ,  B32B3/266 ,  B32B2307/102 ,  B32B2605/18 ,  B64D33/02 ,  B64D2033/0206 ,  F02C7/045 ,  G10K11/168 ,  G10K11/172

Abstract: An acoustic treatment panel including a porous acoustically resistive structure which includes at least one external layer which is in contact with the external environment and which has through holes, internal strips including several openings which communicate with the inside of the cells of the panel and connecting canals, interposed between the external layer and the internal strips, which ensure that the floor-section openings communicate with at least one through hole of the external layer.

公开(公告)号：US20180283320A1

公开(公告)日：2018-10-04

申请号：US15927822

申请日：2018-03-21

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

Inventor： Nicolas Jolivet

IPC: F02K1/76 ,  F02K1/72

Abstract: A nacelle for a turbofan including a mobile cowl mobile in translation between a closing position and an opening position, a window on the upstream side by a fixed cowl and on the downstream side by the mobile cowl, and a reverser flap in rotation between a closed position and an open position. The nacelle includes a locking system with a groove fixed to the mobile cowl and extending between a first end and a second end, and a guided element mounted guided in the slide and fixed to the reverser flap, the guided element moving from the second end towards the first end with cowl movement and leaving the groove when the reverser flap begins rotation, and the guided element moving outside the groove while the reverser flap pivots from the positions and entering the groove at the end of rotation of the reverser flap.

公开(公告)号：US20180281982A1

公开(公告)日：2018-10-04

申请号：US15938014

申请日：2018-03-28

Applicant: Airbus Operations S.A.S.

Inventor： Patrick Zaccaria ,  Sébastien Tranchard

IPC: B64D31/06

Abstract: A method and a device for controlling an aircraft propulsion assembly which mitigates the drawbacks of the application of a protection mode in which the maximum thrust is reduced (a degraded operating mode), in particular when an emergency situation occurs or the switch to protection mode is due to an incorrect analysis of the operating parameters of the propulsion assembly. The method includes a sequence of positions of the thrust control consisting in bringing the thrust control to idle then to setting it into the position corresponding to the desired thrust or a setting of the control to the maximum thrust position. Other simple sequences may include, the transition through the idling position with a transition to maximum thrust position, or through a succession of positions relative to the current position of the thrust control at the moment of the switch to degraded mode.

公开(公告)号：US10088055B2

公开(公告)日：2018-10-02

申请号：US15378866

申请日：2016-12-14

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

Inventor： David Kaslin

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

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：US10081433B2

公开(公告)日：2018-09-25

申请号：US14926908

申请日：2015-10-29

Applicant: Airbus Operations S.A.S.

Inventor： Jacques Hervé Marche

IPC: B64D27/00 ,  B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/262 ,  B64D2027/264 ,  B64D2027/266

Abstract: A front engine attachment, intended to fix an engine to a structure of an aircraft, includes a first attachment including a base intended to be fixed to the structure, a first fixture articulated on the base, two first connecting rods, each being articulated by a first end to the engine and by a second end to the fixture, and a first cylindrical nose mounted on the base. The front engine attachment includes a second attachment including a cradle including an orifice into which the cylindrical nose is fitted, and a second cylindrical nose being threaded into a piercing of the engine, and two second connecting rods, each being intended to be articulated by a first end to the engine, and by a second end to the cradle.

公开(公告)号：US20180247009A1

公开(公告)日：2018-08-30

申请号：US15965318

申请日：2018-04-27

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

Inventor： François Rouyre ,  Pascal Chaumel ,  Samuel Burgunder

IPC: G06F17/50 ,  G06T7/30 ,  G06T17/00 ,  G06T7/00

CPC classification number: G06F17/5095 ,  G06F17/50 ,  G06F2217/14 ,  G06F2217/16 ,  G06T7/001 ,  G06T7/30 ,  G06T17/005 ,  G06T2207/10024 ,  G06T2207/10028 ,  G06T2207/20072 ,  G06T2207/30164 ,  G06T2219/012

Abstract: Method and system of simple, precise, rapid and automatic control to verify fit between a manufactured device and its digital mock-up modelling it beforehand. The system includes a scanner configured to produce a three-dimensional cloud of points representative of the device, as well as a processor and a memory configured to superpose the cloud of points on the digital mock-up, coordinate the cloud of points with polychrome images captured during the scanning of the device and stored in a memory, disperse the cloud of points into several sets of points, each set of points corresponding to an object identified in the polychrome images, establish a correspondence between the sets of points and nodes of a treelike structure identifying the digital mock-up, and evaluate a fit between the cloud of points and the digital mock-up by analyzing the correspondence between the sets of points and the nodes of the treelike structure.