公开(公告)号：US10020690B2

公开(公告)日：2018-07-10

申请号：US15033960

申请日：2014-10-30

Applicant: Airbus SAS

Inventor： Nicolas Colin ,  Didier Simonet

IPC: H01F27/42 ,  H02J50/15 ,  H02J50/80 ,  B64C39/02 ,  H02J17/00 ,  H02J7/02 ,  H02J50/10 ,  G01S19/13

CPC classification number: H02J50/15 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/145 ,  G01S19/13 ,  H02J7/025 ,  H02J17/00 ,  H02J50/10 ,  H02J50/80

Abstract: The invention consists of a system allowing remote wireless transfer of energy from a base station to a moving object, in particular a drone, moving in a given zone around the base station. The system includes means for tracking the moving object so as to determine the position of the moving object relative to the base station at any time, means for transmitting a synthetic acoustic wave focused in the direction of the moving object, these two means being located at the base station and powered by the base station, and acoustic reception means, located on the moving object, for receiving the acoustic wave transmitted by the base station and converting the received acoustic wave into an electrical signal and then into a power supply voltage for a battery.

公开(公告)号：US20180170568A1

公开(公告)日：2018-06-21

申请号：US15834605

申请日：2017-12-07

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

Inventor： Alain Porte ,  Patrick Oberle ,  Gregory Albet

IPC: B64D33/02 ,  B64F5/40

Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment. Thus, the air input lip has a lighter structure.

公开(公告)号：US20180106216A1

公开(公告)日：2018-04-19

申请号：US15785012

申请日：2017-10-16

Applicant: Airbus Operations SAS ,  Airbus SAS

Inventor： Nicolas JOLIVET ,  Franck OUNDJIAN ,  Frédéric PIARD ,  Vincent BILLEROT ,  Benoit LETAY ,  Patrick OBERLE ,  Thomas SAUVALLE ,  Thierry SURPLY ,  Alain PORTE

IPC: F02K1/62 ,  F02K1/76

CPC classification number: F02K1/62 ,  B64D29/02 ,  F02K1/72 ,  F02K1/763 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2250/313 ,  F05D2260/53

Abstract: A nacelle for a ducted fan turbojet engine comprising an engine. The nacelle comprises a fixed cowl, an upstream wall bounding off, with the engine, a working section for a secondary flow, a movable cowl with an interior wall and an exterior wall, and movable in translation between a closing position where the exterior wall adjoins the fixed cowl and the interior wall prolongs the upstream wall, and an opening position where the exterior wall is distant from the fixed cowl so as to open a window and the interior wall is distant from the upstream wall, an inverter flap between the interior wall and the exterior wall mounted to be free in rotation about an axis of rotation situated on the interior wall and a drive mechanism for moving the movable cowl.

公开(公告)号：US09932129B2

公开(公告)日：2018-04-03

申请号：US14898128

申请日：2014-06-11

Applicant: AIRBUS SAS

Inventor： Emmanuel Joubert ,  Charles Nespoulous ,  Bruno Rechain ,  Hichem Smaoui

IPC: B64F1/04 ,  B64C25/32 ,  B64F1/22

CPC classification number: B64F1/04 ,  B64C25/32 ,  B64F1/22 ,  B64F1/228 ,  Y02T50/826

Abstract: A device for moving aircraft along the ground includes at least one runway and at least one aircraft. The aircraft is secured to a tractor element having a magnetic mass formed mainly of type II superconductor material and the runway includes stator coils arranged in the runway with at least one line of coils parallel to an axis of the runway. A command/control system supplies power to the stator coils to generate a magnetic field that levitates the tractor element, magnetized beforehand into a phase II superconducting state, above the runway.

公开(公告)号：US09587670B2

公开(公告)日：2017-03-07

申请号：US13891305

申请日：2013-05-10

Applicant: AIRBUS SAS

Inventor： Mickaël Matignon ,  Francis Ramond

IPC: F16C11/06 ,  B64F5/00 ,  B66C1/10

CPC classification number: F16C11/06 ,  B64F5/10 ,  B64F5/50 ,  B66C1/10 ,  Y10T403/32 ,  Y10T403/32631

Abstract: A fitting for an aircraft bracing device including anchor points, wherein the fitting includes a face able to press against the aircraft and at least one guide hole for a connecting element able to collaborate with an anchor point, a slider able to move in a translational movement parallel to a first direction parallel to the face of the fitting and a connection between the slider and the connecting element which allows a movement in a second direction different from the first direction and parallel to the face of the fitting so as to align the connecting element with an anchor point.

Abstract translation: 一种用于包括锚定点的飞机支撑装置的配件，其中所述配件包括能够抵靠所述飞行器的表面和用于能够与锚定点协作的连接元件的至少一个引导孔，能够在平移运动中移动的滑块 平行于与配件的表面平行的第一方向以及滑块和连接元件之间的连接，其允许沿与第一方向不同的第二方向并且平行于配件的表面移动，以便将连接元件 有一个锚点。

公开(公告)号：US20160368606A1

公开(公告)日：2016-12-22

申请号：US15185474

申请日：2016-06-17

Applicant: Airbus Operations GmbH ,  Airbus Operations SAS ,  AIRBUS SAS

Inventor： Dietrich LAMPE ,  Kai CHRISTENSEN ,  Claude CUILLER ,  Pierre-Eric DEREUX ,  Frank FEEST ,  Hyung-Jo KIM ,  Knut NIEMECK ,  Kathryn WAIDELICH

IPC: B64D9/00 ,  B64C1/20 ,  B64C1/22

CPC classification number: A61C19/003 ,  A61C1/0015 ,  A61C19/004 ,  B64C1/20 ,  B64C1/22 ,  B64D9/00 ,  B64D2009/006

Abstract: A device and method for moving cargo above a floor inside an aircraft comprises a rigid under-floor. The device comprises a body part for supporting the weight of the cargo, lifting means and for lowering the body part from its lifted position into a retracted position, and a drive unit for moving the body part . The method comprises the steps of providing at least two devices in an aircraft, positioning the devices beneath the cargo, wherein the body parts of the devices are in their retracted positions. The body parts are lifted such that the weight of the cargo is supported by the body parts and the cargo is lifted above the floor. The cargo is then moved to a desired position and lowered into their retracted positions such that the cargo is lowered and the devices are moved away vertically from the cargo.

Abstract translation: 用于将货物运送到飞机内的地板上方的装置和方法包括刚性地板。 该装置包括用于支撑货物重量的主体部分，提升装置和用于将主体部分从其提升位置降低到缩回位置，以及用于使主体部分移动的驱动单元。 该方法包括以下步骤：在飞行器中提供至少两个装置，将装置定位在货物下方，其中装置的主体部分处于其缩回位置。 身体部分被提起，使得货物的重量由身体部位支撑并且货物被提升到地板上方。 然后将货物移动到期望的位置并降低到其缩回位置，使得货物下降并且将装置从货物垂直移开。

公开(公告)号：US20160318623A1

公开(公告)日：2016-11-03

申请号：US15141068

申请日：2016-04-28

Applicant: Airbus Operations (SAS) ,  Airbus SAS

Inventor： Patrick Zaccaria ,  Emmanuele Costanzo ,  Laurent Bouin

IPC: B64D45/00 ,  B64D31/06

CPC classification number: B64D45/00 ,  B64D31/06 ,  B64D2045/0085 ,  F02C9/00 ,  F05D2260/80

Abstract: An aircraft comprising at least two engines and an electronic management arrangement comprising a control computer for each engine, each computer being configured for monitoring the operation of its associated engine and for activating an engine protection mode when the engine operation exceeds predetermined operational limits The electronic management arrangement furthermore comprises an engine interface device to which the control computers are connected, the device prohibiting the activation of a protection mode by a control computer when a protection mode is activated by another control computer. A monitoring device is connected to the control computers and receives an information signal from each control computer to indicate if a protection mode is activated and transmits, in the case where a protection mode is activated on at least two engines, a control signal to the control computer having last activated a protection mode to cancel the activation of the protection mode.

Abstract translation: 一种包括至少两个发动机的飞行器和包括用于每个发动机的控制计算机的电子管理装置，每个计算机被配置为用于监视其相关联的发动机的操作以及当发动机操作超过预定操作限制时启动发动机保护模式。电子管理 还包括控制计算机连接到的引擎接口装置，当由另一控制计算机激活保护模式时，该装置禁止控制计算机启动保护模式。 监视装置连接到控制计算机，并且从每个控制计算机接收信息信号以指示是否激活保护模式，并且在至少两个发动机上激活保护模式的情况下，发送控制信号 计算机最后激活保护模式以取消激活保护模式。

公开(公告)号：US20160214736A1

公开(公告)日：2016-07-28

申请号：US15005387

申请日：2016-01-25

Applicant: Airbus (SAS) ,  Airbus Operations (SAS)

Inventor： Philippe Perrin ,  Matthias Eberle

IPC: B64D45/04 ,  B64D47/02 ,  B64D45/00

CPC classification number: B64D45/04 ,  B64D45/0005 ,  B64D47/02 ,  G05D1/0676 ,  G05D1/085 ,  G08G5/0021 ,  G08G5/025

Abstract: A device for assisting in the landing of an aircraft in a flare phase comprising a control stick, a first unit for acquiring current flight parameters of the aircraft, a second unit for acquiring a current deflection angle of the control stick, a computation unit for computing a difference between the current deflection angle of the control stick and a target deflection angle of the control stick, and an acoustic emission unit configured to automatically emit a warning or guidance sound signal in the cockpit of the aircraft, according to the difference between the current deflection angle and the target deflection angle of the control stick.

Abstract translation: 一种用于辅助飞机着陆的装置，包括控制棒，用于获取飞行器的当前飞行参数的第一单元，用于获取控制棒的当前偏转角的第二单元，用于计算的计算单元 控制棒的当前偏转角与控制棒的目标偏转角之间的差异，以及声发射单元，被配置为根据当前的电流之间的差自动地发出飞行器的驾驶舱中的警告或引导声音信号 偏转角和控制棒的目标偏转角。

公开(公告)号：US09401094B2

公开(公告)日：2016-07-26

申请号：US14790574

申请日：2015-07-02

Applicant: Airbus (SAS)

Inventor： Christophe Cros ,  Vincent Loubiere ,  Alexandre Godin

IPC: G08G5/04 ,  G08G5/06 ,  H04N5/232 ,  G06K9/46 ,  H04N5/247 ,  B64D47/08 ,  G06F3/038 ,  G02B27/01 ,  G06T19/00 ,  G06T15/20 ,  G06K9/00 ,  G08G5/00 ,  H04N7/18

CPC classification number: G08G5/045 ,  B64D47/08 ,  G02B27/017 ,  G02B2027/0178 ,  G06F3/0383 ,  G06K9/00791 ,  G06K9/00805 ,  G06K9/46 ,  G06T15/20 ,  G06T19/006 ,  G08G5/0021 ,  G08G5/065 ,  H04N5/23238 ,  H04N5/23293 ,  H04N5/247 ,  H04N7/18

Abstract: A method for assisting the piloting of an aircraft on the ground comprises the steps of obtaining a panoramic view of at least one area adjacent to the aircraft, isolating an image corresponding to a part of the panoramic view and which is selected according to an orientation desired by the pilot, and displaying the image on a display device visible by the pilot. A system for the implementation of the method is also provided.

Abstract translation: 一种用于协助在地面上飞行的飞行员的方法包括以下步骤：获得与飞行器相邻的至少一个区域的全景视图，隔离与全景视图的一部分相对应的图像，并根据所需的取向选择 并且在飞行员可见的显示装置上显示图像。 还提供了一种用于实现该方法的系统。

公开(公告)号：US09248905B2

公开(公告)日：2016-02-02

申请号：US13894944

申请日：2013-05-15

Applicant: AIRBUS OPERATIONS S.L. ,  AIRBUS SAS

Inventor： Ludovic Gerard ,  Alejandro Gutiérrez García ,  Julián Maldonado

IPC: B64C23/00 ,  B64C25/16 ,  B64D41/00 ,  B64C25/00

CPC classification number: B64C23/005 ,  B64C25/16 ,  B64C2025/003 ,  B64D41/007 ,  B64D2201/00

Abstract: An aircraft (11) with at least an inflatable device (41) installed in a cavity (21) in its external surface which is equipped with a door (25) for opening/closing said cavity (21) is provided. The inflatable device (41), comprising a cushion (45) and a gas generator is configured for filling the cavity (21) with the cushion (45) when it is inflated with the gas supplied by said gas generator, without protruding from the cavity (21) for reducing the downstream air flow disturbances generated by said cavity (21) when the door (25) is open. The inflatable device (41) includes control means for inflating the cushion (45) in predetermined circumstances, being the door (25) open. The invention is particularly applicable to the cavities of the Main Landing Gear (31) for avoiding power losses to a Ram Air Turbine (51) placed behind it.

Abstract translation: 提供一种具有安装在其外表面中的空腔（21）中的至少一个可充气装置（41）的飞行器（11），其配备有用于打开/关闭所述空腔（21）的门（25）。 包括衬垫（45）和气体发生器的充气装置（41）构造成当用气体发生器供应的气体充气时，利用衬垫（45）填充空腔（21），而不会从空腔 （21），用于当门（25）打开时减小由所述空腔（21）产生的下游空气流动干扰。 充气装置（41）包括控制装置，用于在门（25）打开的情况下在预定情况下使垫子（45）充气。 本发明特别适用于主起落架（31）的空腔，用于避免向放置在其后面的拉姆空气涡轮机（51）的功率损失。