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1.发明授权公开(公告)号：US08550399B2
公开(公告)日：2013-10-08
申请号：US12681836
申请日：2008-09-29
IPC分类号： B64C1/00
CPC分类号： B64C1/068 , B64C1/12 , B64C2001/0072 , Y02T50/43
摘要： A fuselage structure for an aircraft fuselage in composite material and an aircraft including such a fuselage structure. The fuselage structure provides savings in mass while allowing grounding of electric systems, and with which substantial mechanical stiffness characteristics may be guaranteed. In the fuselage structure attachment modules provide an assembling function as well as an electric function.
摘要翻译： 用于复合材料中飞机机身的机身结构和包括这种机身结构的飞机。 机身结构提供了质量的节省，同时允许电气系统的接地，并且可以保证其具有显着的机械刚度特性。 在机身结构中，附件模块提供组装功能以及电气功能。
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公开(公告)号：US09180625B2
公开(公告)日：2015-11-10
申请号：US13546441
申请日：2012-07-11
CPC分类号： B29C70/207 , B29B11/16 , B29C70/222 , B29C70/342 , B29C70/345 , B29L2031/3082 , Y02T50/43
摘要： A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform (22), and deforming the flat preform (22) in such a way as to produce the three-dimensional preform, with the fibers following suitable trajectories at the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.
摘要翻译： 一种用于生产由双曲面复合材料制成的飞行器面板的方法，其特征在于，由三维预成型件获得，所述三维预成型件包括以限定的布置分布的纤维，包括制造扁平纤维预制件（22），以及 使扁平预成型件（22）变形，以便制造三维预成型件，其中纤维在平坦预制件上按照合适的轨迹，以便获得变形后的纤维的限定布置。
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3.发明申请FUSELAGE STRUCTURE FOR AN AIRCRAFT FUSELAGE IN COMPOSITE MATERIAL AND AIRCRAFT EQUIPPED WITH SUCH A FUSELAGE STRUCTURE 有权复合材料中的飞机熔接的熔敷结构和装有这种熔融结构的飞机公开(公告)号：US20100264273A1
公开(公告)日：2010-10-21
申请号：US12681836
申请日：2008-09-29
CPC分类号： B64C1/068 , B64C1/12 , B64C2001/0072 , Y02T50/43
摘要： A fuselage structure for an aircraft fuselage in composite material and an aircraft including such a fuselage structure. The fuselage structure provides savings in mass while allowing grounding of electric systems, and with which substantial mechanical stiffness characteristics may be guaranteed. In the fuselage structure attachment modules provide an assembling function as well as an electric function.
摘要翻译： 用于复合材料中飞机机身的机身结构和包括这种机身结构的飞机。 机身结构提供了质量的节省，同时允许电气系统的接地，并且可以保证其具有显着的机械刚度特性。 在机身结构中，附件模块提供组装功能以及电气功能。
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公开(公告)号：US20130180642A1
公开(公告)日：2013-07-18
申请号：US13724475
申请日：2012-12-21
申请人： Philippe BLOT , Laurent GIUSEPPIN , Bernard DUPRIEU , Cyrille COLLART , Sébastien ALBY , Jean-Pierre CABANAC
发明人： Philippe BLOT , Laurent GIUSEPPIN , Bernard DUPRIEU , Cyrille COLLART , Sébastien ALBY , Jean-Pierre CABANAC
IPC分类号： B64F5/00
CPC分类号： B64F5/10 , B29C70/342 , B29C70/865 , B29D99/0014 , Y10T156/10
摘要： The invention provides a self-stiffened composite panel including an external skin, an internal skin superposed on the external skin, which covers an internal face of the external skin and at least one stiffener protruding inwards relatively to the internal skin which extends along a longitudinal direction, characterised in that the stiffener is made as one piece with the internal skin and consists of a portion of the internal skin which is located at distance from the external skin. The invention also provides a process for making such a self-stiffened panel.
摘要翻译： 本发明提供了一种自加强复合板，其包括外皮，重叠在外皮上的内皮，其覆盖外皮的内表面，以及至少一个相对于沿着纵向方向延伸的内皮向内突出的加强件 其特征在于，所述加强件与所述内部皮肤制成一体，并且由位于所述外部皮肤的距离处的所述内部皮肤的一部分组成。 本发明还提供了制造这种自加强板的方法。
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公开(公告)号：US20130015602A1
公开(公告)日：2013-01-17
申请号：US13546441
申请日：2012-07-11
IPC分类号： B29C53/04
CPC分类号： B29C70/207 , B29B11/16 , B29C70/222 , B29C70/342 , B29C70/345 , B29L2031/3082 , Y02T50/43
摘要： A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform (22), and deforming the flat preform (22) in such a way as to produce the three-dimensional preform, with the fibers following suitable trajectories at the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.
摘要翻译： 一种用于生产由双曲面复合材料制成的飞行器面板的方法，其特征在于，由三维预成型件获得，所述三维预成型件包括以限定的布置分布的纤维，包括制造扁平纤维预制件（22），以及 使扁平预成型件（22）变形，以便制造三维预成型件，其中纤维在平坦预制件上按照合适的轨迹，以便获得变形后的纤维的限定布置。
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