公开(公告)号：US20160152315A1

公开(公告)日：2016-06-02

申请号：US14952376

申请日：2015-11-25

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

Inventor： Esteban MARTINO GONZALEZ ,  Diego FOLCH CORTES ,  Pablo GOYA ABAURREA ,  Angel PASCUAL FUERTES ,  Sandra LINARES MENDOZA ,  Julien GUILLEMAUT ,  Eric BOUCHET ,  Jerome COLMAGRO ,  Jonathan BLANC

IPC: B64C1/06 ,  B64C3/32 ,  B64C1/12

CPC classification number: B64C1/061 ,  B64C1/06 ,  B64C1/12 ,  B64C1/16 ,  B64C1/26 ,  B64C3/32

Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.

Abstract translation: 一种包括适于位于机身周边内的中心元件的飞行器机身框架，以及从作为提升表面的纵向结构的一部分的中心元件的两侧突出到机身的周边外侧的两个侧向延伸部。 中心元件和两个横向延伸部被配置为一体的部件。

公开(公告)号：US20160311515A1

公开(公告)日：2016-10-27

申请号：US14695731

申请日：2015-04-24

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

Inventor： Julien GUILLEMAUT ,  Esteban MARTINO GONZALEZ ,  Diego FOLCH CORTES ,  Jerome COLMAGRO ,  Jonathan BLANC

IPC: B64C1/16 ,  B64C1/12 ,  B64F5/00 ,  B64C1/06

CPC classification number: B64C1/061 ,  B64C1/26 ,  B64D27/14

Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.

Abstract translation: 在配备有穿过机身的发动机安装结构的飞机后部的情况下，后部的组装呈现出通过机身中的横向开口移动安装结构而引起的问题。 为了克服这些问题，提出了一种组装飞机后部的方法，其中发动机安装结构的箱体结构通过从机身的一侧延伸到另一侧的顶部开口插入到机身中， 机身的垂直中平面，使得顶部开口通向机身的顶部和侧面。

公开(公告)号：US20180170563A1

公开(公告)日：2018-06-21

申请号：US15845330

申请日：2017-12-18

Applicant: Airbus Operations SAS ,  Airbus Operations SL

Inventor： Eric BOUCHET ,  Esteban MARTINO-GONZALEZ ,  Jerome COLMAGRO ,  Fernando INIESTA LOZANO ,  Julien MOULIS ,  Antoine ABELE

IPC: B64D27/20 ,  B64C1/16 ,  B64D27/26

CPC classification number: B64D27/20 ,  B64C1/061 ,  B64C1/16 ,  B64D27/14 ,  B64D27/26 ,  B64D2027/268 ,  B64D2033/0286 ,  Y02T50/44

Abstract: In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.

公开(公告)号：US20180066606A1

公开(公告)日：2018-03-08

申请号：US15693735

申请日：2017-09-01

Applicant: Airbus Operations (SAS)

Inventor： Olivier PAUTIS ,  Jerome COLMAGRO

IPC: F02K1/72 ,  F02K1/76

CPC classification number: F02K1/72 ,  F02K1/763 ,  F05D2260/50

Abstract: A thrust reverser system with a thrust reverser cascade and a reverser door with door segments laid out in a folded condition relatively to each other in an inactive configuration of the reverser system, and accommodated in an accommodation space located outside the secondary channel. Upon passing from the inactive configuration to the active configuration a rearward displacement of the cascade towards a nacelle aperture, released by an external movable nacelle cowl driven rearwards by the cascade, and a deployment of segments until they attain a deployed closing position within the secondary channel occurs simultaneously.