公开(公告)号：US20160229513A1

公开(公告)日：2016-08-11

申请号：US15018481

申请日：2016-02-08

Applicant: Airbus Operations (SAS) ,  Airbus Operations GmbH ,  Airbus Operations S.L.

Inventor： Henning Scheel ,  Eric Bouchet ,  Julien Guillemaut ,  Esteban Martino-Gonzalez

IPC: B64C1/14 ,  B64C1/16 ,  B64C1/10

CPC classification number: B64C1/1446 ,  B64C1/10 ,  B64C1/16 ,  B64D27/14 ,  B64D27/20 ,  B64D29/08 ,  B64D37/005 ,  B64D2041/002 ,  Y02T50/44

Abstract: An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.

Abstract translation: 飞机尾锥包括机身，其中安装有航空电子设备。 尾锥包括形成在机身中的两个横向舱口，至少一个舱口形成在机身的两个相对的两侧上。 每个舱口相对于机身可移除地安装，以便收起闭合的第一位置，其中舱口关闭机身中的侧向开口，以及打开的第二位置，打开的舱口允许进入尾锥体的内部 通过相应的开口需要定期检查和/或维护操作的航空电子设备被容纳在尾锥的一部分中，该尾锥可以通过机身中的两个侧向开口接近留在机身外部的人。

公开(公告)号：US10124876B2

公开(公告)日：2018-11-13

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 ,  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.

公开(公告)号：US09656736B2

公开(公告)日：2017-05-23

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: B64C1/06 ,  B64C1/26

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.

公开(公告)号：US09359085B2

公开(公告)日：2016-06-07

申请号：US13724360

申请日：2012-12-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Diego Folch Cortés ,  Eduardo Vinué Santolalla ,  Esteban Martino González ,  Julien Guillemaut ,  Pablo Goya Abaurrea

IPC: B64D45/00 ,  B64C1/06 ,  B64D27/14 ,  B64D27/02 ,  B64C1/10 ,  B64D27/20 ,  B64D27/00

CPC classification number: B64D45/00 ,  B64C1/06 ,  B64C1/10 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D2027/005 ,  Y02T50/66

Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

Abstract translation: 具有由安装在其每侧的两个发动机形成的推进系统的飞行器的后机身中的内部盾构; 后机身至少具有垂直对称平面; 后机身由复合材料制成; 所述内部屏蔽件位于所述垂直对称平面中，并且延伸在覆盖一组预定义片段的可能轨迹的区域中，所述一组预先定义的片段在将影响相对发动机的关键元件的故障事件中与所述发动机中的一个分离; 内部屏蔽具有平坦的形状和能量吸收能力，其允许停止所述碎片。 本发明还涉及一种用于确定内部屏蔽件和具有所述内部屏蔽件的飞行器的面积的方法。