公开(公告)号：US20130214090A1

公开(公告)日：2013-08-22

申请号：US13724360

申请日：2012-12-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Diego FOLCH CORTÉS ,  Eduardo VINUÉ SANTOLALLA ,  Esteban MARTINO GONZALEZ ,  Julien GUILLEMAUT ,  Pablo GOYA ABAURREA

IPC: B64D45/00 ,  B64D27/02

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。

公开(公告)号：US20180127081A1

公开(公告)日：2018-05-10

申请号：US15803559

申请日：2017-11-03

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

Inventor： Javier TORAL VÁZQUEZ ,  Esteban MARTINO GONZALEZ ,  Diego FOLCH CORTES ,  Pablo GOYA ABAURREA ,  Vasillis VOTSIOS ,  Michel FOUINNETAU ,  Sylvain ROUMEGAS

IPC: B64C1/12 ,  B32B5/02 ,  B32B5/18 ,  B64C5/02 ,  B64F5/10

CPC classification number: B64C1/12 ,  B32B5/028 ,  B32B5/18 ,  B32B2305/30 ,  B32B2305/38 ,  B32B2605/18 ,  B64C3/28 ,  B64C5/02 ,  B64C2001/0072 ,  B64D2045/0095 ,  B64F5/10

Abstract: A panel structure for an aircraft with at least one composite layer, and at least one net-shaped layer attached to the composite layer, wherein the net-shaped layer has a material suitable to improve the impact resistance of the panel structure. The net-shaped layer can be used to attach two composite layers. Alternatively, the net-shaped layer can be attached to a surface of one composite layer. In this last case, the net-shaped layer may be joined to a laminate sheet material and filled with a foam material. An impact reinforced panel structure is disclosed capable of withstanding any impact, such as a blade release, or a bird strike, without substantially modifying the manufacturing process.

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：US20160185465A1

公开(公告)日：2016-06-30

申请号：US14975338

申请日：2015-12-18

Applicant: AIRBUS OPERATIONS, S.A.S. ,  AIRBUS OPERATIONS S.L.

Inventor： Javier TORAL VÁZQUEZ ,  Diego FOLCH CORTES ,  Esteban MARTINO GONZÁLEZ ,  Pablo GOYA ABAURREA ,  Vasillis VOTSIOS ,  Michel FOUINNETAU ,  Sylvain ROUMEGAS

IPC: B64D45/00 ,  B64C11/16

CPC classification number: B64C11/20

Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.

Abstract translation: 一种适于安装在螺旋桨叶片中的自毁装置，所述自毁装置包括适于检测所述螺旋桨叶片的释放的检测器，适于在检测器检测到释放的情况下发送释放警报的警告机构 螺旋桨叶片，以及在从警告机构接收到释放报警的情况下适于破坏螺旋桨叶片的破坏机构。 还提供发动机和飞机。