公开(公告)号：US20170066518A1

公开(公告)日：2017-03-09

申请号：US15259585

申请日：2016-09-08

Applicant: Airbus Operations SAS ,  Airbus Operations S.L.

Inventor： Guillaume Gallant ,  Jose Luis Martinez Munoz

IPC: B64C1/06 ,  B64D29/06 ,  B64D41/00 ,  B64C5/02

CPC classification number: B64C1/068 ,  B64C1/069 ,  B64C1/26 ,  B64C5/02 ,  B64C5/06 ,  B64D29/06 ,  B64D41/00 ,  B64D2041/002

Abstract: To optimize the structure of an aircraft tail section, an aircraft rear section comprises a fuselage section, a tail section, and a vertical stabilizer comprising a box-section structure which comprises a box-section upper part extending on the outside of the tail section, and a box-section lower part housed inside the tail section, such that the tail section is wholly supported by the box-section structure.

Abstract translation: 为了优化飞机尾部的结构，飞机后部包括机身部分，尾部和垂直稳定器，其包括箱部结构，该箱部结构包括在尾部的外侧延伸的箱部上部， 以及容纳在尾部内的箱部下部，使得尾部完全由箱部结构支撑。

公开(公告)号：US10167081B2

公开(公告)日：2019-01-01

申请号：US14139295

申请日：2013-12-23

Applicant: Airbus Operations (SAS)

Inventor： Guillaume Gallant ,  Romain Delahaye

IPC: B64C39/10 ,  B64D9/00 ,  B64C1/14 ,  B64F1/30 ,  B64F1/32 ,  B64D11/00 ,  B64C1/00

Abstract: Optimization of the use of the available volume in a flying wing for commercial passenger transport, in particular for short- or medium-haul routes. A flying wing is provided including a passenger cabin together with at least one hold for the transport of luggage and/or goods, in which the hold is positioned laterally relative to said passenger cabin.

公开(公告)号：US09840321B2

公开(公告)日：2017-12-12

申请号：US14966478

申请日：2015-12-11

Applicant: Airbus Operations (SAS)

Inventor： Guillaume Gallant ,  Herve Biennes

IPC: B64C25/16 ,  B64C1/06 ,  B64F5/00 ,  B64C1/10 ,  B64C25/10 ,  B64C25/14

CPC classification number: B64C25/16 ,  B64C1/068 ,  B64C1/10 ,  B64C25/10 ,  B64C25/14 ,  B64F5/00

Abstract: In order to assist fitting of doors to the landing gear housing and adjusting their position, an aircraft nose is provided comprising a connecting frame between the landing gear housing and the outer skin of the fuselage, the connecting frame extending around an opening in the outer skin and comprising a skirt bearing against the outer skin of the fuselage and attached thereto, the skirt defining a passage for landing gear which is configured to be closed off by doors when the landing gear are in a closed position, and supporting members extending between the fuselage and the doors.

公开(公告)号：US20140175218A1

公开(公告)日：2014-06-26

申请号：US14139153

申请日：2013-12-23

Applicant: Airbus Operations (SAS)

Inventor： Guillaume Gallant ,  Romain Delahaye

IPC: B64D9/00 ,  B64C1/26 ,  B64C1/14 ,  B64D37/04

CPC classification number: B64D9/00 ,  B64C1/00 ,  B64C1/1484 ,  B64C1/26 ,  B64C2001/0045 ,  B64D37/04

Abstract: An aircraft of which the transversal section of the fuselage is reduced optimally at the price of a reduced carrying capacity of luggage or merchandise but adapted to short- and medium-haul type routes. The fuselage has for this purpose lateral protuberances defining storage areas arranged on either side of a passenger cabin and able to house luggage and/or merchandise, and/or onboard service equipment, and/or removable fuel tanks.

Abstract translation: 飞机的机身横截面以最小的行李箱或商品的承载能力降低，但适用于短途和中程航线的方式最优化。 机身为此目的设置横向突起，其定义了存放在客舱两侧的储存区域，并且能够容纳行李和/或商品，和/或船上服务设备和/或可拆卸的燃料箱。

公开(公告)号：US09637234B2

公开(公告)日：2017-05-02

申请号：US14139153

申请日：2013-12-23

Applicant: Airbus Operations (SAS)

Inventor： Guillaume Gallant ,  Romain Delahaye

IPC: B64D9/00 ,  B64D37/04 ,  B64C1/22 ,  B64C1/14 ,  B64C1/26 ,  B64C1/00

CPC classification number: B64D9/00 ,  B64C1/00 ,  B64C1/1484 ,  B64C1/26 ,  B64C2001/0045 ,  B64D37/04

Abstract: An aircraft of which the transversal section of the fuselage is reduced optimally at the price of a reduced carrying capacity of luggage or merchandise but adapted to short- and medium-haul type routes. The fuselage has for this purpose lateral protuberances defining storage areas arranged on either side of a passenger cabin and able to house luggage and/or merchandise, and/or onboard service equipment, and/or removable fuel tanks.

公开(公告)号：US20160176513A1

公开(公告)日：2016-06-23

申请号：US14966478

申请日：2015-12-11

Applicant: Airbus Operations (SAS)

Inventor： Guillaume Gallant ,  Herve Biennes

IPC: B64C25/16 ,  B64F5/00 ,  B64C1/06

CPC classification number: B64C25/16 ,  B64C1/068 ,  B64C1/10 ,  B64C25/10 ,  B64C25/14 ,  B64F5/00

Abstract: In order to assist fitting of doors to the landing gear housing and adjusting their position, an aircraft nose is provided comprising a connecting frame between the landing gear housing and the outer skin of the fuselage, the connecting frame extending around an opening in the outer skin and comprising a skirt bearing against the outer skin of the fuselage and attached thereto, the skirt defining a passage for landing gear which is configured to be closed off by doors when the landing gear are in a closed position, and supporting members extending between the fuselage and the doors.

Abstract translation: 为了有助于将门安装到起落架壳体并调整其位置，提供飞行器鼻部，其包括在起落架壳体和机身的外表皮之间的连接框架，连接框架围绕外皮的开口延伸 并且包括裙部，其抵靠机身的外皮并附接到其上，所述裙部限定起落架通道，该起落架构造成在起落架处于关闭位置时由门关闭，以及在机身之间延伸的支撑构件 和门。

公开(公告)号：US09308711B2

公开(公告)日：2016-04-12

申请号：US13677557

申请日：2012-11-15

Applicant: Airbus Operations SAS

Inventor： Julien Charles ,  Guillaume Gallant ,  Denis Soula

IPC: B32B7/04 ,  B29C65/08 ,  B32B37/00 ,  B32B38/00 ,  B26D1/547 ,  B29C65/76 ,  B29C65/00 ,  B29L31/30

CPC classification number: B32B38/0004 ,  B26D1/547 ,  B29C65/08 ,  B29C65/76 ,  B29C66/0044 ,  B29C66/112 ,  B29C66/114 ,  B29C66/30223 ,  B29C66/532 ,  B29C66/721 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/8122 ,  B29C66/81427 ,  B29C66/8322 ,  B29C2793/009 ,  B29L2031/3076 ,  Y10T83/04 ,  Y10T428/24479 ,  B29K2827/18

Abstract: A method for disassembling two ultrasonically welded elements, one of the elements comprising, at a surface opposite the other element, an energy director that concentrates the heating during ultrasonic welding and forms a material junction between the two assembled elements after the ultrasonic welding. The method includes the steps of positioning a wire between the two assembled elements, so as to be secant to the energy director, said wire having suitable mechanical characteristics allowing it to cut the junction formed by the energy director and moving the wire between the two assembled elements so as to cut said junction.

公开(公告)号：US11420761B2

公开(公告)日：2022-08-23

申请号：US16898960

申请日：2020-06-11

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

Inventor： Matthieu Thomas ,  Anthony Roux ,  Didier Poirier ,  Olivier Verseux ,  André Anger ,  Benedikt Bammer ,  Guido Klewer ,  Guillaume Gallant ,  Florian Vogel ,  Christian Wehle

IPC: B64D35/02 ,  B60L50/71 ,  B64C5/06 ,  B64D27/24 ,  B64D29/02 ,  B64D31/02 ,  B60L58/30 ,  B64C3/32 ,  B64D33/10 ,  B64D37/08 ,  B64D41/00

Abstract: An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

公开(公告)号：US20160176532A1

公开(公告)日：2016-06-23

申请号：US14977049

申请日：2015-12-21

Applicant: Airbus Operations (SAS)

Inventor： Julien Guillemaut ,  Guillaume Gallant

IPC: B64D27/14 ,  B64C11/06 ,  B64C11/20

CPC classification number: B64D27/14 ,  B64C11/001 ,  B64C11/06 ,  B64C11/20 ,  B64D2027/005 ,  Y02T50/66

Abstract: A propeller for a turbomachine intended to be driven in rotation about a propeller rotation axis and including variable pitch blades. The propeller further includes a structure for radial retention of the blades in the event of them breaking. The retaining structure extends around the propeller rotation axis and has the aerodynamic part of each blade of the propeller pass through it. Moreover, each aerodynamic part is equipped with an abutment configured to be retained radially by the retaining structure in the event of a blade fracture causing a fracture in the aerodynamic part radially inside the abutment.

Abstract translation: 用于涡轮机的推进器旨在围绕螺旋桨旋转轴线旋转并且包括可变桨距叶片。 螺旋桨还包括用于在它们断裂的情况下径向保持叶片的结构。 保持结构围绕螺旋桨旋转轴线延伸，并且螺旋桨的每个叶片的空气动力学部分通过它。 此外，每个空气动力部件配备有一个邻接构造，以在叶片断裂的情况下由保持结构径向地保持，从而在邻接部的径向内部的空气动力部分中断裂。

公开(公告)号：US20140175215A1

公开(公告)日：2014-06-26

申请号：US14139295

申请日：2013-12-23

Applicant: Airbus Operations (SAS)

Inventor： Guillaume Gallant ,  Romain Delahaye

IPC: B64D9/00 ,  B64F1/32 ,  B64D11/06 ,  B64F1/30 ,  B64C39/10 ,  B64C1/14

CPC classification number: B64C39/10 ,  B64C1/1423 ,  B64C2001/0036 ,  B64C2039/105 ,  B64D9/00 ,  B64D9/003 ,  B64D11/00 ,  B64F1/30 ,  B64F1/32

Abstract: Optimization of the use of the available volume in a flying wing for commercial passenger transport, in particular for short- or medium-haul routes. A flying wing is provided including a passenger cabin together with at least one hold for the transport of luggage and/or goods, in which the hold is positioned laterally relative to said passenger cabin.

Abstract translation: 优化在飞行飞机上使用可用体积的商业客运，特别是短途或中程航路。 提供了一个飞翼，包括一个乘客舱以及至少一个用于运送行李和/或货物的托架，其中保持件相对于所述客舱横向定位。