公开(公告)号：US20160152315A1

公开(公告)日：2016-06-02

申请号：US14952376

申请日：2015-11-25

申请人： Airbus Operations S.L. ,  Airbus Operations SAS

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

IPC分类号： B64C1/06 ,  B64C3/32 ,  B64C1/12

CPC分类号： B64C1/061 ,  B64C1/06 ,  B64C1/12 ,  B64C1/16 ,  B64C1/26 ,  B64C3/32

摘要： 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.

摘要翻译： 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：US20130214090A1

公开(公告)日：2013-08-22

申请号：US13724360

申请日：2012-12-21

申请人： AIRBUS OPERATIONS S.L.

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

IPC分类号： B64D45/00 ,  B64D27/02

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

摘要： 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.

摘要翻译： 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：US20160311515A1

公开(公告)日：2016-10-27

申请号：US14695731

申请日：2015-04-24

申请人： Airbus Operations (S.A.S.) ,  Airbus Operations, S.L.

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

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

CPC分类号： B64C1/061 ,  B64C1/26 ,  B64D27/14

摘要： 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.

摘要翻译： 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：US20180127081A1

公开(公告)日：2018-05-10

申请号：US15803559

申请日：2017-11-03

申请人： Airbus Operations, S.L. ,  Airbus Operations (S.A.S.)

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

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

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

摘要： 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：US20170058985A1

公开(公告)日：2017-03-02

申请号：US15247013

申请日：2016-08-25

申请人： Airbus Operations S.L.

发明人： Esteban MARTINO GONZALEZ ,  Andrea Iván MARASCO ,  Diego FOLCH CORTÉS ,  Javier TORAL VÁZQUEZ ,  Vasilis VOTSIOS ,  Raúl FERNANDEZ BALLESTEROS ,  Fernando PEREIRA MOSQUEIRA

IPC分类号： F16F7/12 ,  G10K11/16 ,  F16F7/00

CPC分类号： F16F7/12 ,  B29C44/357 ,  B29K2995/0002 ,  B29K2995/0091 ,  B29L2009/00 ,  B29L2031/30 ,  B29L2031/60 ,  B32B1/08 ,  B32B3/12 ,  B32B3/18 ,  B32B25/00 ,  B32B2250/03 ,  B32B2307/102 ,  B32B2307/51 ,  B32B2307/56 ,  B32B2307/734 ,  B32B2605/18 ,  F16F3/00 ,  F16F7/00 ,  F16F7/121 ,  G10K11/16

摘要： A deformable structure, such as a panel or a shock absorber, for absorbing energy from a mechanical and/or acoustic impact. The structure comprises an inner core and one or more external layers covering the inner core. The inner core comprises a set of first segments having a positive Poison's ratio and second segments having a negative Poisson's ratio. The first and second segments are arranged alternately and joined to one another so that the deformation received by one first segment is transmitted to an adjacent second segment and vice versa.

摘要翻译： 用于从机械和/或声学冲击中吸收能量的可变形结构，例如面板或减震器。 该结构包括内芯和覆盖内芯的一个或多个外层。 内芯包括具有正毒力比的一组第一段和具有负泊松比的第二段。 第一和第二段交替地布置并且彼此连接，使得由一个第一段接收的变形被传递到相邻的第二段，反之亦然。