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公开(公告)号：EP3318481B1
公开(公告)日：2020-07-08
申请号：EP16382507.8
申请日：2016-11-04
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公开(公告)号：EP3248864B1
公开(公告)日：2019-07-03
申请号：EP16382226.5
申请日：2016-05-24
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公开(公告)号：EP3318481A1
公开(公告)日：2018-05-09
申请号：EP16382507.8
申请日：2016-11-04
发明人： TORAL VAZQUEZ, Javier , MARTINO GONZALEZ, Esteban , FOLCH CORTES, Diego , GOYA ABAURREA, Pablo , VOTSIOS, Vasilis , FOUINNETAU, Michel , ROUMEGAS, Sylvain
摘要： The invention refers to a panel structure (1) for an aircraft comprising at least one composite layer (3, 4), and at least one net-shaped layer (2) attached to the at least one composite layer (3, 4), wherein the net-shaped layer (2) comprises a material suitable to improve the impact resistance of the panel structure (1). The net-shaped layer (2) can be used to attach two composite layers (3, 4). Alternatively, the net-shaped layer (2) can be attached to a surface of one composite layer (3, 4). In this last case, the net-shaped layer (2) may be joined to a laminate sheet material (5), and filled with a foam material (6). The invention provides an impact reinforced panel structure (1) capable of withstanding any impact, such as a blade release, or a bird strike, without substantially modifying the manufacturing process.
摘要翻译： 本发明涉及一种用于飞行器的面板结构（1），其包括至少一个复合层（3,4）和至少一个附着到所述至少一个复合层（3,4）的网状层（2） 其中所述网状层（2）包括适于改善所述面板结构（1）的抗冲击性的材料。 网状层（2）可用于连接两个复合层（3,4）。 或者，网状层（2）可以附着到一个复合层（3,4）的表面。 在这最后一种情况下，网状层（2）可以接合到层压片材料（5）上，并填充有泡沫材料（6）。 本发明提供了一种抗冲击增强面板结构（1），其能够承受诸如刀片释放或鸟撞击之类的任何冲击，而基本不改变制造过程。
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公开(公告)号：EP3530561A1
公开(公告)日：2019-08-28
申请号：EP18382119.8
申请日：2018-02-27
发明人： MARTINO-GONZALEZ, Esteban , VELEZ DE MENDIZABAL ALONSO, Iker , VOTSIOS, Vasilis , NICOLAS GUTIERREZ, Guillermo , SANCHEZ FRANCO, Diego , MATESANZ HIDALGO, David , HERNANZ-MANRIQUE, Jose Angel
摘要： Auxetic bi-stable structure that comprises:
- an auxetic curved shell (2) movable between a first and a second stable position, and
- a rigid element (1) wherein at least part of the surface the auxetic curved shell (2) is joined to the rigid element (1) such that the curved shell (2) is movable with respect to said rigid element (1) between said first and second stable positions.-
5.发明公开DEFORMABLE STRUCTURE FOR ABSORPTION OF ENERGY FROM MECHANICAL AND/OR ACOUSTIC IMPACTS 审中-公开可变形结构，用于吸收能量机械和/或声学效果
公开(公告)号：EP3135949A1
公开(公告)日：2017-03-01
申请号：EP15382432.1
申请日：2015-08-27
发明人： MARTINO GONZALEZ, Esteban , MARASCO, Andrea Iván , PEREIRA MOSQUEIRA, Fernando , FOLCH CORTÉS, Diego , TORAL VÁZQUEZ, Javier , VOTSIOS, Vasilis , FERNANDEZ BALLESTEROS, Raúl
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： The invention provides a deformable structure, such as a panel (11) or a shock absorber (20), for absorbing energy from a mechanical and/or acoustic impact comprising an inner core (13) and one or more external layers covering the inner core (13). The inner core (13) comprises a set of first segments (25) having a positive Poison's ratio and second segments (35) having a negative Poisson's ratio. The first and second segments (25, 35) are arranged alternately and joined between them so that the deformation received by one first segment (25) can be transmitted to an adjacent second segment (35) and vice versa.
摘要翻译： 本发明提供一种可变形结构，检查作为面板（11）或一个减震器（20），用于从机械和/或声学冲击吸收能量，包括内芯（13）和一个或多个外部层覆盖所述内芯的 （13）。 内芯（13）包括一组第一部段（25），具有正的泊松比和具有负泊松比第二区段（35）的。 在第一和第二分段（25,35）交替地设置，并在它们之间接合，从而也被一个第一区段（25）接收到的变形可以是反式mitted在相邻的第二区段（35），并且反之亦然。
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6.发明公开AIRCRAFT WITH A PROTECTIVE SHIELD AGAINST AN ENGINE BLADE RELEASE 审中-公开FLUGZEUG MIT EINEM SCHUTZSCHILD GEGEN EINE MOTORSCHAUFELFREISETZUNG
公开(公告)号：EP3106381A1
公开(公告)日：2016-12-21
申请号：EP15382311.7
申请日：2015-06-15
发明人： TORAL VÁZQUEZ, Javier , MARTINO GONZÁLEZ, Esteban , FOLCH CORTÉS, Diego , GOYA ABAURREA, Pablo , VOTSIOS, Vasilis , FOUINNETAU, Michel , ROUMEGAS, Sylvain , BROCHARD, Wolfgang
摘要： The invention provides an internal shield (31) inside the rear fuselage (11) of an aircraft having a propulsion system formed by two engines (13) mounted on each side of it. The internal shield (31) is located in a suitable place inside the rear fuselage (11) for covering the possible trajectories of fragments detached from one of said engines (13) in a failure event that would impact critical elements of the opposite engine. The internal shield (31) comprises an ensemble of fluid containers belonging to aircraft sub-systems, such us particularly the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping said fragments. The invention also refers to an aircraft having said internal shield (31).
摘要翻译： 本发明提供了一种具有由安装在其每侧的两个发动机（13）形成的推进系统的飞行器的后机身（11）内部的内部屏蔽（31）。 内部屏蔽（31）位于后部机身（11）内的合适位置，用于在会影响到相反发动机的关键元件的故障事件中覆盖与所述发动机（13）之一分离的碎片的可能轨迹。 内部屏蔽（31）包括属于飞机子系统的流体容器的集合，特别是饮用水和废水子系统，具有足够的流体，用于提供停止所述碎片所需的能量吸收能力。 本发明还涉及具有所述内部屏蔽（31）的飞行器。
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公开(公告)号：EP3135949B1
公开(公告)日：2019-06-19
申请号：EP15382432.1
申请日：2015-08-27
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公开(公告)号：EP3106381B1
公开(公告)日：2018-10-24
申请号：EP15382311.7
申请日：2015-06-15
发明人： TORAL VÁZQUEZ, Javier , MARTINO GONZÁLEZ, Esteban , FOLCH CORTÉS, Diego , GOYA ABAURREA, Pablo , VOTSIOS, Vasilis , FOUINNETAU, Michel , ROUMEGAS, Sylvain , BROCHARD, Wolfgang
摘要： The invention provides an internal shield (31) inside the rear fuselage (11) of an aircraft having a propulsion system formed by two engines (13) mounted on each side of it. The internal shield (31) is located in a suitable place inside the rear fuselage (11) for covering the possible trajectories of fragments detached from one of said engines (13) in a failure event that would impact critical elements of the opposite engine. The internal shield (31) comprises an ensemble of fluid containers belonging to aircraft sub-systems, such us particularly the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping said fragments. The invention also refers to an aircraft having said internal shield (31).
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公开(公告)号：EP3248864A1
公开(公告)日：2017-11-29
申请号：EP16382226.5
申请日：2016-05-24
发明人： VELEZ DE MENDIZABAL ALONSO, Iker , GUINALDO FERNANDEZ, Enrique , GARCÍA NIETO, Carlos , HONORATO RUIZ, Francisco, Javier , VOTSIOS, Vasilis
CPC分类号： B64C3/28 , B64D7/00 , B64D2033/022
摘要： The invention refers to an aerodynamic surface (1) for an aircraft comprising a torsion box having a front spar (5), and a composite leading edge section that comprises an outer surface (2) shaped with an aerodynamic leading edge profile, an inner surface (3) internally arranged with respect to the outer surface (2), and a blanket (4) spanwise arranged between the outermost point of the inner surface (3) and the front spar (5), wherein the blanket is made of fibre material having a specific energy absorption ranging from 47 to 72 J•g- 1 and a longitudinal wave speed ranging from 6 to 15 km•s -1 , wherein the major part of the blanket (4) is of dry fibre material, and wherein the blanket (4) is joined to at least two opposing areas of the inner surface (3) for absorbing a bird strike, to prevent the damage of the front spar (5).
摘要翻译： 本发明涉及一种用于飞行器的空气动力学表面（1），其包括具有前翼梁（5）的扭转箱以及复合前缘部分，所述复合前缘部分包括形成有空气动力学前缘轮廓的外表面（2），内表面 （3）相对于外表面（2）内部布置，以及在内表面（3）的最外点和前翼梁（5）之间翼展布置的橡皮布（4），其中橡皮布由纤维材料 具有47至72J·g -1的特定能量吸收和6至15km·s-1的纵波速度，其中，橡皮布（4）的主要部分是干纤维材料，并且其中 橡皮布（4）连接到内表面（3）的至少两个相对区域以吸收鸟击，以防止前翼梁（5）的损坏。
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