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公开(公告)号：US11131243B2
公开(公告)日：2021-09-28
申请号：US16281799
申请日：2019-02-21
Applicant: Airbus Operations S.L.
Inventor： Esteban Martino-Gonzalez , Iker Velez De Mendizabal Alonso , Vasilis Votsios , Guillermo Nicolas Gutierrez , Diego Sanchez Franco , David Matesanz Hidalgo , Jose Angel Hernanz-Manrique
Abstract: An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.
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公开(公告)号：US20160362167A1
公开(公告)日：2016-12-15
申请号：US15182672
申请日：2016-06-15
Applicant: Airbus Operations S.L. , Airbus Operations S.A.S.
Inventor： Javier Toral Vazquez , Esteban Martino Gonzalez , Diego Folch Cortes , Pablo Goya Abaurrea , Vasilis Votsios , Michel Fouinnetau , Sylvain Roumegas , Wolfgang Brochard
Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.
Abstract translation: 飞机后部机身内部有一个内部屏蔽罩，它具有由安装在其两侧的两个发动机构成的推进系统。 内部防护罩位于后机身内部的合适位置，用于覆盖可能影响对方发动机的关键元件的故障事件中与其中一个发动机分离的碎片的可能轨迹。 内部屏蔽件包括属于飞行器子系统的流体容器的集合体，特别是饮用水和废水子系统，具有足够的流体，用于提供停止碎片所需的能量吸收能力。 还公开了具有内部屏蔽的飞机。
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Patent Agency Ranking
公开(公告)号：US10023299B2
公开(公告)日：2018-07-17
申请号：US14757591
申请日：2015-12-23
Applicant: AIRBUS OPERATIONS, S.L.
Inventor： Javier Toral Vazquez , Diego Folch Cortes , Esteban Martino Gonzalez , Pablo Goya Abaurrea , Vasilis Votsios , Michel Fouinnetau , Sylvain Roumegas
Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.
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公开(公告)号：US10730602B2
公开(公告)日：2020-08-04
申请号：US15182672
申请日：2016-06-15
Applicant: Airbus Operations S.L. , Airbus Operations SAS
Inventor： Javier Toral Vazquez , Esteban Martino Gonzalez , Diego Folch Cortes , Pablo Goya Abaurrea , Vasilis Votsios , Michel Fouinnetau , Sylvain Roumegas , Wolfgang Brochard
Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.
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公开(公告)号：US09995359B2
公开(公告)日：2018-06-12
申请号：US15247013
申请日：2016-08-25
Applicant: Airbus Operations S.L.
Inventor： Esteban Martino Gonzalez , Andrea Iván Marasco , Diego Folch Cortés , Javier Toral Vázquez , Vasilis Votsios , Raúl Fernandez Ballesteros , Fernando Pereira Mosqueira
CPC classification number: 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
Abstract: 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.
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公开(公告)号：US20160176509A1
公开(公告)日：2016-06-23
申请号：US14757591
申请日：2015-12-23
Applicant: Airbus Operations, S.L.
Inventor： Javier Toral Vazquez , Diego Folch Cortes , Esteban Martino Gonzalez , Pablo Goya Abaurrea , Vasilis Votsios , Michel Fouinnetau , Sylvain Roumegas
CPC classification number: B64C11/26 , B64D2201/00
Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.
Abstract translation: 本发明涉及一种用于飞行器发动机的螺旋桨叶片，其包括包含在叶片内部并包括至少一个袋和至少一个气体发生器的气囊系统，所述至少一个气体发生器与至少一个袋流体连通，用于使 袋，用于检测叶片的一部分破裂的检测系统，用于当由检测系统检测到破裂时启动至少一个气体发生器的触发器，并且叶片皮肤被配置为允许至少一个袋子 穿过叶片皮肤，以在气体发生器的袋子充气时在叶片外部膨胀。
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公开(公告)号：US20160161223A1
公开(公告)日：2016-06-09
申请号：US14963535
申请日：2015-12-09
Applicant: AIRBUS OPERATIONS, S.A.S. , AIRBUS OPERATIONS, S.L.
Inventor： Javier Toral Vazques , Pablo Goya Abaurrea , Esteban Martino Gonzalez , Diego Folch Cortes , Vasilis Votsios , Michel Fouinnetau
IPC: F41H5/04
CPC classification number: F41H5/0485 , D03D1/0052
Abstract: The disclosure refers to an impact protective multi-layered fabric comprising a pile of layers of a dry-fabric material, wherein at least one of the layers is conformed to have least one closed fold extending longitudinally across the layer, the closed fold having first and second walls substantially facing each other, and wherein the first and second walls are stitched to each other by means of at least one yarn of a dry-fabric material. According to an aspect, the first and second walls of the closed fold, are stitched to each other by means of two or more stitching lines are arranged one above the other within the closed fold, such as when an object impact on the fabric layer, the stitches of the stitching lines break sequentially one after the other, such the energy absorption capability of the layer is increased in a simple manner and without increasing its weight.
Abstract translation: 本公开涉及一种防冲击保护性多层织物，其包括一堆干织物材料层，其中至少一层被配合为具有纵向延伸穿过该层的至少一个闭合折叠，封闭折叠具有第一和第 第二壁基本上彼此相对，并且其中第一和第二壁通过至少一根干织物材料的纱线彼此缝合。 根据一个方面，通过两个或更多个缝合线将闭合折叠的第一和第二壁彼此缝合，所述两条或更多条缝合线在闭合折叠内彼此上下排列，例如当物体对织物层的冲击时， 缝合线的线迹依次断开，层的能量吸收能力以简单的方式增加，而不增加其重量。
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