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61. 发明授权

EP1984645B1 FORCE LEVEL CONTROL FOR AN ENERGY ABSORBER FOR AIRCRAFT 有权
标题翻译：功率电平控制FOR ENERGY SHOCKS FOR飞机
公开(公告)号：EP1984645B1
公开(公告)日：2016-08-17
申请号：EP07703165.6
申请日：2007-01-31
申请人： Airbus Operations GmbH
发明人： HUMFELDT, Dirk , HARRIEHAUSEN, Michael , SCHRÖDER, Jan , SPERBER, Martin , DEMARY, Michael
IPC分类号： F16F7/12 , B64D11/00
CPC分类号： B60R22/28 , B64C1/062 , B64D25/04 , F16F7/123 , F16F7/128

62. 发明公开

EP3053823A1 An aircraft with a subfloor region that accommodates an auxiliary compartment 有权
标题翻译： FLUGZEUG MIT EINEM UNTERBODENABSCHNITT ZUR UNTERBRINGUNG EINES ZUSATZFACHS
公开(公告)号：EP3053823A1
公开(公告)日：2016-08-10
申请号：EP15400006.1
申请日：2015-02-06
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Behrens, Michael , Wahnfried, Markus , Löser, Frank , Mores, Sebastian
IPC分类号： B64C1/06 , B64C1/18 , B64D1/22 , B64D37/04
CPC分类号： B64C1/18 , B64C1/062 , B64D1/22 , B64D9/00 , B64D37/04 , B64D45/00
摘要： The invention is related to an aircraft (1) with a fuselage (2) and a floor structure (3c) that is arranged inside said fuselage (2), said floor structure (3c) and said fuselage (2) defining a subfloor region (4) between said floor structure (3c) and a fuselage underside (2a) of said fuselage (2), said subfloor region (4) accommodating at least one auxiliary compartment (6b), wherein an equipment bay (7) with at least one auxiliary equipment (8) is arranged within said subfloor region (4), said at least one auxiliary equipment (8) being at least essentially stowable in said equipment bay (7) in a stow mode and said at least one auxiliary compartment (6b) being at least partly arranged in a region between said equipment bay (7) and said floor structure (3c) such that said at least one auxiliary compartment (6b) separates said equipment bay (7) from said floor structure (3c).
摘要翻译：本发明涉及一种具有机身（2）的飞机（1）和布置在所述机身（2）内的地板结构（3c），所述地板结构（3c）和所述机身（2）限定底板区域 4）位于所述机身（2）的所述地板结构（3c）和机身下侧（2a）之间，所述地板下部区域（4）容纳至少一个辅助隔间（6b），其中设有具有至少一个辅助设备（8）布置在所述地板下部区域（4）内，所述至少一个辅助设备（8）至少基本上可收起在所述设备舱（7）中，并且所述至少一个辅助舱室（6b）至少部分地布置在所述设备隔间（7）和所述地板结构（3c）之间的区域中，使得所述至少一个辅助隔室（6b）将所述设备间隔（7）与所述地板结构（3c）分离。

63. 发明公开

EP2558360A2 LUFTFAHRZEUG MIT EINER INTEGRIERTEN ENERGIEAUFNEHMENDEN VERFORMUNGSSTRUKTUR UND LUFTFAHRZEUG MIT EINEM DERARTIGEN RUMPF 有权转让
标题翻译：具有集成能接收成形结构和飞机这样的船体飞机HULL
公开(公告)号：EP2558360A2
公开(公告)日：2013-02-20
申请号：EP11718921.7
申请日：2011-04-09
申请人： Premium AEROTEC GmbH
发明人： MAYER, Franziskus , MEISNER, Christoph , STARKE, Peter
IPC分类号： B64C1/06
CPC分类号： B64C1/062
摘要： An aircraft fuselage with an integrated energy-absorbing deformation structure, wherein the fuselage (1) has annular frames (10; 110; 210) and the frames (10; 110; 210) have interconnecting longitudinal fuselage beams (12) and a casing (14) forming a fuselage skin (16; 116; 216), wherein, in the interior of the fuselage (1), there is provided at least one lower floor structure (3; 103; 203), which has a plurality of transverse beams (32; 132; 232), connected to an assigned frame (10; 110; 210), and longitudinal floor beams (4, 5, 30; 104, 105; 204, 205), interconnecting these transverse beams, and wherein the deformation structure is formed in a lower region of the fuselage that is situated below the lower floor structure (3; 103; 203), is distinguished by the fact that the deformation structure comprises a first inelastically deformable central region (20; 120; 220) and, respectively on the left side and on the right side, a second inelastically deformable region (26, 28; 126, 128; 226, 228) of greater stiffness in the vertical direction than the central region.

64. 发明授权

EP2219941B1 DISPOSITIF DE LIAISON ENTRE UNE PIÈCE DE STRUCTURE INTERNE D'UN AÉRONEF ET LE FUSELAGE DE CELUI-CI 失效
标题翻译：连接装置，用于连接飞机结构部件船体该平面
公开(公告)号：EP2219941B1
公开(公告)日：2012-08-08
申请号：EP08872099.0
申请日：2008-11-14
申请人： AIRBUS OPERATIONS
发明人： DEPEIGE, Alain
IPC分类号： B64C1/12 , B64C1/06 , B64C1/14
CPC分类号： B64C1/062 , B64C1/12 , B64C1/1461
摘要： Aircraft comprising at least one door (14, 16 P1) for passengers to board the aircraft, characterized in that it comprises at least one interconnection device (20; 40; 50; 60; 70) connecting an aircraft internal structure component (24) and a skin of the fuselage (22) of the aircraft, the interconnection device being positioned near the internal periphery of the door in a region (Z1) subject to external knocks and comprising at least one region that is weakened in terms of compression (26c; 42a; 42b; 62b; 62c; 62d; 72b; 74b) so as to absorb the knocks experienced by the external face of the skin of the fuselage, the device also being configured to withstand tensile forces applies to the internal face of the skin of the fuselage by the internal pressure inside the aircraft.

65. 发明公开

EP2243701A2 Impact-absorbing structure and method for producing the same 有权
标题翻译： AufpralldämpfendeStruktur und Herstellungsverfahrendafür
公开(公告)号：EP2243701A2
公开(公告)日：2010-10-27
申请号：EP10159744.1
申请日：2010-04-13
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： Tanaka, Atsumi , Maruyama, Hironori , Kanemasu, Masayuki
IPC分类号： B64C1/06
CPC分类号： B64C1/062 , B29C65/483 , B29C65/5057 , B29C66/721 , B29C70/086 , B29C70/865 , B29C70/88 , B29K2063/00 , B29K2067/00 , B29K2067/06 , B29K2069/00 , B29K2075/00 , B29K2077/00 , B29K2077/10 , B29K2079/08 , B29K2101/10 , B29K2101/12 , B29K2105/06 , B29K2277/10 , B29K2305/00 , B29K2307/00 , B29K2307/02 , B29K2309/04 , B29K2309/08 , B29K2707/04 , B29K2995/0089 , B29L2031/3076 , B29L2031/608 , Y02T50/43 , Y10T156/10
摘要： An object is to provide an impact-absorbing structure superior in impact-absorbing capacity. An impact-absorbing structure includes a pair of flat, plate-like face plates (19) arranged to oppose each other with a predetermined distance therebetween; a core member (17) arranged between the face plates and fixed to the face plates; and a composite-material tube arranged between the face plates (7), at the core member side, the impact-absorbing member extending in one direction and fracturing progressively due to an impact compression force acting in the one direction. The composite-material tube is fixed to the face plates at one portion constituting a bonded region and is allowed to move relative to the face plates at a remaining portion constituting a non-bonded region.
摘要翻译：目的在于提供一种冲击吸收能力优异的冲击吸收结构。冲击吸收结构包括一对扁平的板状面板（19），它们以彼此相对的间隔彼此相隔预定距离; 芯片构件，其布置在所述面板之间并固定到所述面板; 以及复合材料管，其布置在所述面板（7）之间，在所述芯部件侧，所述冲击吸收部件沿一个方向延伸并且由于沿所述一个方向作用的冲击压缩力而逐渐断裂。复合材料管在构成接合区域的一部分处固定到面板，并且在构成非接合区域的剩余部分处允许复合材料管相对于面板移动。

66. 发明公开

EP2219941A2 DISPOSITIF DE LIAISON ENTRE UNE PIÈCE DE STRUCTURE INTERNE D'UN AÉRONEF ET LE FUSELAGE DE CELUI-CI 失效
标题翻译：连接装置，用于连接飞机结构部件船体该平面
公开(公告)号：EP2219941A2
公开(公告)日：2010-08-25
申请号：EP08872099.0
申请日：2008-11-14
申请人： AIRBUS OPERATIONS
发明人： DEPEIGE, Alain
IPC分类号： B64C1/12 , B64C1/06 , B64C1/14
CPC分类号： B64C1/062 , B64C1/12 , B64C1/1461
摘要： Aircraft comprising at least one door (14, 16 P1) for passengers to board the aircraft, characterized in that it comprises at least one interconnection device (20; 40; 50; 60; 70) connecting an aircraft internal structure component (24) and a skin of the fuselage (22) of the aircraft, the interconnection device being positioned near the internal periphery of the door in a region (Z1) subject to external knocks and comprising at least one region that is weakened in terms of compression (26c; 42a; 42b; 62b; 62c; 62d; 72b; 74b) so as to absorb the knocks experienced by the external face of the skin of the fuselage, the device also being configured to withstand tensile forces applies to the internal face of the skin of the fuselage by the internal pressure inside the aircraft.

67. 发明授权

EP1963177B1 SAFETY SYSTEM FOR REDUCING THE IMPACT ENERGY OF A CONTAINER 有权
标题翻译：保障体系，减轻收盘能源集装箱
公开(公告)号：EP1963177B1
公开(公告)日：2010-02-10
申请号：EP06841003.4
申请日：2006-12-15
申请人： Airbus Operations GmbH
发明人： MERZ, Ludger , FUHRMANN, Roland
IPC分类号： B64C1/10 , B64D9/00
CPC分类号： B64C27/006 , B64C1/062 , B64D9/00 , B64D9/003 , B64D2201/00 , Y02T50/46

68. 发明公开

EP2117922A2 COMPLIANT PANEL FOR AIRCRAFT 有权
标题翻译：柔性板FOR A平面
公开(公告)号：EP2117922A2
公开(公告)日：2009-11-18
申请号：EP08731565.1
申请日：2008-03-06
申请人： The Boeing Company
发明人： KOCH, William J. , MATHESON, Donald, P. , ANDERSON, Barney, B. , SWADA, Jeffrey, R.
IPC分类号： B64C1/10 , B64C1/12
CPC分类号： B64C1/10 , B64C1/062 , B64C1/12
摘要： A pressurized bulkhead or panel for an aircraft includes an energy absorbing skin that deforms in response to an object strike that imparts at least a threshold amount of impact energy to the skin. The skin may be configured as a dome or a lofted panel that is essentially free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristics of the skin. The skin may be formed from a monolithic one-piece material, such as metal of composites, and may include various integrally formed reinforcing features.

69. 发明公开

EP2046636A1 ENCADREMENT DE PORTE POUR AERONEF 失效转让
标题翻译：飞机门
公开(公告)号：EP2046636A1
公开(公告)日：2009-04-15
申请号：EP07823651.0
申请日：2007-07-26
申请人： AIRBUS France
发明人： LARCHER, David
IPC分类号： B64C1/14
CPC分类号： B64C1/1461 , B64C1/062
摘要： The invention concerns a doorway (1) in an aircraft fuselage (2) comprising a door frame in which a door is mounted, this frame comprising an outer framework (60), an inner framework (50) and a core (40) placed between the inner framework and the outer framework, capable of absorbing energy from an impact, the core (40) being a stiffener made of composite material having an accordion shape.

70. 发明授权

EP1777155B1 Deformable floor substructure for a helicopter 有权转让
标题翻译：变形的地板下部结构中，直升机
公开(公告)号：EP1777155B1
公开(公告)日：2008-12-10
申请号：EP05425743.1
申请日：2005-10-21
申请人： Agusta S.p.A.
发明人： Poggi, Stefano
IPC分类号： B64C1/00 , B64C1/18 , B64C27/00
CPC分类号： F16F7/12 , B64C1/062 , B64C1/18 , B64C27/006

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