公开(公告)号：US20230406476A1

公开(公告)日：2023-12-21

申请号：US18337139

申请日：2023-06-19

Applicant: Airbus Operations SAS

Inventor： Anthony MERTES ,  Patrick LIEVEN

IPC: B64C1/12

CPC classification number: B64C1/12

Abstract: An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.

公开(公告)号：US20210163116A1

公开(公告)日：2021-06-03

申请号：US16953832

申请日：2020-11-20

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Christophe MIALHE ,  Jérôme PHALIPPOU

IPC: B64C1/14 ,  B64C1/00 ,  B64C1/06

Abstract: A windshield for an aircraft cockpit is provided which includes a glazed windshield part which has a single curvature corresponding to a portion of the envelope of a cone extending between a lower plane and an upper plane which intersect an axis of the cone. The single curvature of the glazed part of the windshield enables the glazed part to be produced more easily, for example by rolling or by hydroforming. It also makes it possible to create configurations for a cockpit for two pilots, a single pilot or even no pilot, on the basis of a single aerodynamic shape of the fuselage of the aircraft by only adapting the structure of the windshield. Also provided are a windshield frame for such a windshield, a windshield assembly including such a windshield frame and such a windshield, and an aircraft equipped with such a windshield.

公开(公告)号：US20250026465A1

公开(公告)日：2025-01-23

申请号：US18769034

申请日：2024-07-10

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Edmond FROGER

IPC: B64C1/06 ,  B64C1/26

Abstract: An assembly comprising at least first and second components, at least one connection element comprising a rod configured to ensure uptake of the traction/compression forces between the first and second components, and at least one pair of first and second contact surfaces provided respectively with first and second bumps and rigidly secured respectively to the first and second components, the first and second bumps having complementary shapes configured to nest in one another and ensure transmission of the shear forces between the first and second components. Also, an aircraft comprising at least one such assembly.

公开(公告)号：US20240262486A1

公开(公告)日：2024-08-08

申请号：US18428366

申请日：2024-01-31

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Anthony MERTES ,  Flavio Ferreira RAIMUNDO

IPC: B64C1/14

CPC classification number: B64C1/1461

Abstract: An access door assembly for a fuselage having a structure delimiting an access hatch, an upper part and a lower part of an access door, hinges fastened between the structure and the upper part in the vicinity of an upper edge, a guiding system between the lower part and the structure and guiding the lower part in translation, upper locks between the upper part and the lower part and/or the structure and lower locks between the lower part and the structure.

公开(公告)号：US20200079489A1

公开(公告)日：2020-03-12

申请号：US16559919

申请日：2019-09-04

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Laurent LACHE ,  Pierre DOUREL

IPC: B64C1/14 ,  E05B17/00

Abstract: In order to simplify the kinematics involved in opening an aircraft door, a plurality of mobile stop members is provided at the periphery of the door, these being intended to press against complementary stop arrangement provided on the door frame. A door control device is configured to bring the door from its closed position into a set-back intermediate position by moving it towards the interior of the compartment, and a stop arrangement control device is configured to allow the mobile stop members to be moved, when the door is occupying its set-back intermediate position, from a deployed locking position to a retracted unlocking position, allowing the door to be moved outward through the opening in the fuselage.

公开(公告)号：US20130320143A1

公开(公告)日：2013-12-05

申请号：US13896754

申请日：2013-05-17

Applicant: Airbus Operations (SAS)

Inventor： Pascal CHAUMEL ,  Patrick LIEVEN ,  Serge CASSAGNES

IPC: B64C1/14

CPC classification number: B64C1/1484

Abstract: The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane.

Abstract translation: 本发明涉及一种飞机窗，其类型包括用于将窗口固定到飞行器的机身上的保持框架和通过密封系统安装在保持框架中的至少一个窗格，所述至少一个窗格具有内表面 和外表面，其特征在于，当所述外表面和所述窗格的内表面之间没有压力差时，所述窗格在处于静止状态的第一状态中包括在其外表面中的至少一个凹部，并且 在第二状态下至少部分根除窗格的至少一个凹面，其中在窗格的外表面和内表面之间存在压力差。

公开(公告)号：US20190300186A1

公开(公告)日：2019-10-03

申请号：US16368305

申请日：2019-03-28

Applicant: Airbus Operations SAS

Inventor： Patrick LIEVEN ,  Jérôme COLMAGRO

IPC: B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  F01D15/10 ,  F02C6/00

Abstract: A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.