公开(公告)号：US20220126985A1

公开(公告)日：2022-04-28

申请号：US17506300

申请日：2021-10-20

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

Inventor： Daniel Bellet ,  Alexandre Legardez

IPC: B64C25/26 ,  B64C25/16 ,  B64C1/06

Abstract: A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

公开(公告)号：US11945575B2

公开(公告)日：2024-04-02

申请号：US17296788

申请日：2020-05-19

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

Inventor： Christopher James Perkins ,  Marco Boscolo ,  Nicholas White ,  Xavier Matheis ,  Alexandre Legardez ,  Simon Roux ,  Sébastien Crouzet

IPC: B64C25/10 ,  B64C25/04

CPC classification number: B64C25/10 ,  B64C25/04

Abstract: A retractable fuselage mounted landing gear assembly is disclosed. The landing gear assembly includes a main strut, a drag stay and a landing gear main fitting. A first end of the drag stay is attached to the main strut and a second end of the drag stay is connected to the fuselage. A first end of the landing main fitting is attached to the main strut and a second end of the main fitting is connected to the fuselage. When the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the fuselage via one or more of the drag stay and the main fitting.

公开(公告)号：US10343768B2

公开(公告)日：2019-07-09

申请号：US14973489

申请日：2015-12-17

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

Inventor： Daniel Bellet ,  Guillaume Gallant ,  François Loyant ,  Alexandre Legardez ,  Simon Roux

IPC: B64C25/04 ,  B64C1/10 ,  B64C1/18 ,  B64C25/12

Abstract: An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing gear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.

公开(公告)号：US09452818B2

公开(公告)日：2016-09-27

申请号：US14100853

申请日：2013-12-09

Applicant: AIRBUS OPERATIONS S.A.S.

Inventor： Francois Loyant ,  Alexandre Legardez

IPC: B64C1/26

CPC classification number: B64C1/26

Abstract: An aircraft comprising a wing box and a fuselage provided with a connecting device configured to be connected to the wing box and to transmit thereto stresses undergone by the fuselage during maneuvers of the aircraft are provided. The connecting device is formed by a keel beam and a keel beam panel connected to the beam via a connecting portion of the beam, that is moreover provided with a main portion extending in a first, generally longitudinal direction and a transfer portion extending in a second direction different from the first direction and configured to be connected to the box. The main, transfer and connecting portions are configured to direct a major part of the stresses received by the beam in the second direction and transmit said major part of the stresses to the box by compression.

Abstract translation: 提供了一种飞机，其包括翼盒和机身，其设置有连接装置，该连接装置被配置为连接到翼盒并且向其传送机身在飞机操作期间经受的应力。 连接装置由龙骨梁和龙骨梁板形成，该龙骨梁和梁梁通过梁的连接部分连接到梁上，其还设置有沿第一大致纵向方向延伸的主要部分和在第二纵向方向上延伸的转移部分 方向与第一方向不同，并且被配置为连接到盒子。 主要的，转移和连接部分构造成引导梁在第二方向上接收的应力的主要部分，并通过压缩将所述大部分应力传递到箱体。

公开(公告)号：US11691717B2

公开(公告)日：2023-07-04

申请号：US17506300

申请日：2021-10-20

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

Inventor： Daniel Bellet ,  Alexandre Legardez

IPC: B64C1/06 ,  B64C25/26 ,  B64C25/16

CPC classification number: B64C25/26 ,  B64C1/068 ,  B64C25/16

Abstract: A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

公开(公告)号：US20140158828A1

公开(公告)日：2014-06-12

申请号：US14100853

申请日：2013-12-09

Applicant: Airbus Operations S.A.S.

Inventor： Francois Loyant ,  Alexandre Legardez

IPC: B64C1/26

CPC classification number: B64C1/26

Abstract: An aircraft comprising a wing box and a fuselage provided with a connecting device configured to be connected to the wing box and to transmit thereto stresses undergone by the fuselage during manoeuvres of the aircraft are provided. The connecting device is formed by a keel beam and a keel beam panel connected to the beam via a connecting portion of the beam, that is moreover provided with a main portion extending in a first, generally longitudinal direction and a transfer portion extending in a second direction different from the first direction and configured to be connected to the box. The main, transfer and connecting portions are configured to direct a major part of the stresses received by the beam in the second direction and transmit said major part of the stresses to the box by compression.

Abstract translation: 提供了一种飞机，其包括翼盒和机身，其设置有连接装置，该连接装置被配置为连接到翼盒并且向其传送机身在飞机操作期间经受的应力。 连接装置由龙骨梁和龙骨梁板形成，该龙骨梁和梁梁通过梁的连接部分连接到梁上，其还设置有沿第一大致纵向方向延伸的主要部分和在第二纵向方向上延伸的转移部分 方向与第一方向不同，并且被配置为连接到盒子。 主要的，转移和连接部分构造成引导梁在第二方向上接收的应力的主要部分，并通过压缩将所述大部分应力传递到箱体。