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公开(公告)号：US20180312239A1
公开(公告)日：2018-11-01
申请号：US15957289
申请日：2018-04-19
发明人： Iker VÉLEZ DE MENDIZÁBAL ALONSO , Esteban MARTINO GONZÁLEZ , David APELLANIZ DE LA FUENTE , Alfonso PARRA RUBIO , Elena MOYA SANZ
CPC分类号： B31D3/0207 , A43B1/0009 , B29D99/0089 , B29K2995/0002 , B29K2995/0091 , B29K2995/0094 , B31D3/005 , B32B3/12 , B33Y80/00 , B64C2001/0072 , B64C2027/4736 , E04C2/36 , F01D5/282
摘要： A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.
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公开(公告)号：US20180170520A1
公开(公告)日：2018-06-21
申请号：US15843203
申请日：2017-12-15
摘要： An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.
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公开(公告)号：US20180072423A1
公开(公告)日：2018-03-15
申请号：US15704114
申请日：2017-09-14
发明人： Iker VÉLEZ DE MENDIZÁBAL ALONSO , Esteban MARTINO GONZÁLEZ , Carlos GARCÍA NIETO , Edouard MENARD , Enrique GUINALDO FERNÁNDEZ , Soledad CRESPO PEÑA , Jesús Javier VÁZQUEZ CASTRO
CPC分类号： B64D7/00 , B32B5/02 , B32B15/14 , B32B2307/558 , B32B2571/02 , B32B2605/18 , B64C1/062 , B64C1/066 , B64C1/12 , F01D21/045 , F41H5/0457 , F41H5/0471
摘要： A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.
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4.发明申请公开(公告)号：US20180174565A1
公开(公告)日：2018-06-21
申请号：US15845281
申请日：2017-12-18
CPC分类号： G10K11/002 , B32B3/12 , F16F7/121
摘要： An energy absorbing structure for attenuating energy received from an energy source. The structure comprises a deformable structure formed by an ensemble of one or more first layers of a material having a positive Poisson's ratio, one or more second layers of a material having a negative Poisson's ratio and one or more third layers of an elastomeric material placed between a first layer and a second layer. The ensemble is arranged with the one or more third layers joined to the first and second layers for absorbing at least part of the energy through shear forces or a combination of traction and compression forces applied to the ensemble by the first and second layers as a consequence of their differential deformation after receiving the energy.
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公开(公告)号：US20180155006A1
公开(公告)日：2018-06-07
申请号：US15801669
申请日：2017-11-02
发明人： Alberto ARANA HIDALGO , Esteban MARTINO GONZÁLEZ , Jesús Javier VÁZQUEZ CASTRO , Pablo CEBOLLA GARROFE
摘要： An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).
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公开(公告)号：US20180281917A1
公开(公告)日：2018-10-04
申请号：US15921399
申请日：2018-03-14
摘要： An impact resistant fuselage of an aircraft, the fuselage extending along a central longitudinal direction, wherein transversal sections of the fuselage are comprised in a vertical plane perpendicular to the central longitudinal direction. The impact resistant fuselage comprises at least a ballistic material membrane extended along the longitudinal direction for absorbing high energy impacts. The membrane according to a transversal section, comprising at least one section between two tensional elements, wherein the material membrane is located inside the fuselage of the aircraft, the at least one section of the membrane is mechanically linked to the inside of the fuselage by the tensional elements, and the two tensional elements stress the membrane.
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7.发明申请公开(公告)号：US20180170513A1
公开(公告)日：2018-06-21
申请号：US15843057
申请日：2017-12-15
摘要： An aircraft rear section (20) including a fuselage rear section (21) extending from the rear pressure bulkhead (23) to the end of the fuselage and an empennage (12) including at least a vertical tail plane (13). An aircraft rear section (20) with a continuous skin (31) is formed by two lateral sides placed symmetrically with respect to the middle vertical plane of the aircraft, each side including an upper portion (26) for the torsion box (14) of the vertical tail plane (13), a lower portion (28) for the fuselage rear section (21) and a transition portion (27) between the upper and lower portions (26, 28). The upper and lower portions (26, 28) of the continuous skin (31) are joined to inner structural components of the vertical tail plane (13) and the fuselage rear section (21).
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公开(公告)号：US20160185465A1
公开(公告)日：2016-06-30
申请号：US14975338
申请日：2015-12-18
发明人： Javier TORAL VÁZQUEZ , Diego FOLCH CORTES , Esteban MARTINO GONZÁLEZ , Pablo GOYA ABAURREA , Vasillis VOTSIOS , Michel FOUINNETAU , Sylvain ROUMEGAS
CPC分类号： B64C11/20
摘要： 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.
摘要翻译： 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。
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