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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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2.发明申请公开(公告)号：US20120193475A1
公开(公告)日：2012-08-02
申请号：US13348110
申请日：2012-01-11
申请人： Jean Pierre CABANAC , Jérôme Colmagro , Jean Marc Durand , Ludovic Fournie , Julien Guillemaut , François Loyant
发明人： Jean Pierre CABANAC , Jérôme Colmagro , Jean Marc Durand , Ludovic Fournie , Julien Guillemaut , François Loyant
IPC分类号： B64C1/26
CPC分类号： B64C1/26
摘要： The stiffening frames (14) of an aircraft fuselage (2) remain continuous while passing through an upper panel (5) of the wing box and extend over the ribs (3) situated in that box. The overall mechanical strength of the assembly is improved, despite the notches it is necessary to make in the panel (5).
摘要翻译： 飞机机身（2）的加强框架（14）在穿过机翼箱的上板（5）时保持连续，并延伸到位于该箱中的肋（3）上。 尽管在面板（5）中需要制作凹口，但组件的整体机械强度得到改善。
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公开(公告)号：US20050121554A1
公开(公告)日：2005-06-09
申请号：US10974537
申请日：2004-10-27
CPC分类号： B29C73/10 , B64C1/1446 , B64F5/10
摘要： A removable plate and a flange that occupies a hole in a panel. The flange has the particular feature of taking up compressive force to which the panel is subjected in its plane, perpendicularly to the hole. The weight of the device used to equip the hole is reduced, and the mechanical behavior of the panel at the position of the hole is improved.
摘要翻译： 一个可移动板和一个占用面板孔洞的法兰。 该凸缘具有吸收面板垂直于孔的平面所承受的压缩力的特征。 用于装备孔的装置的重量减小，并且在孔的位置处的面板的机械性能得到改善。
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4.发明授权公开(公告)号：US08746621B2
公开(公告)日：2014-06-10
申请号：US13348110
申请日：2012-01-11
申请人： Jean Pierre Cabanac , Jerome Colmagro , Jean Marc Durand , Ludovic Fournie , Julien Guillemaut , Francois Loyant
发明人： Jean Pierre Cabanac , Jerome Colmagro , Jean Marc Durand , Ludovic Fournie , Julien Guillemaut , Francois Loyant
IPC分类号： B64C1/06
CPC分类号： B64C1/26
摘要： The stiffening frames (14) of an aircraft fuselage (2) remain continuous while passing through an upper panel (5) of the wing box and extend over the ribs (3) situated in that box. The overall mechanical strength of the assembly is improved, despite the notches it is necessary to make in the panel (5).
摘要翻译： 飞机机身（2）的加强框架（14）在穿过机翼箱的上板（5）时保持连续，并延伸到位于该箱中的肋（3）上。 尽管在面板（5）中需要制作凹口，但组件的整体机械强度得到改善。
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公开(公告)号：US20090294579A1
公开(公告)日：2009-12-03
申请号：US11997834
申请日：2006-07-13
申请人： Olivier Eve , Jean-Pierre Cabanac
发明人： Olivier Eve , Jean-Pierre Cabanac
IPC分类号： B64D27/26
CPC分类号： B64D27/18
摘要： The disclosed embodiments relate to a primary engine strut structure of an aircraft characterized in that it includes single-piece composite panels while replacing the metallic spars and metal panels, the composite panels having a lay-up of fibers oriented along crosswise directions whereby integrating, in the width of the skin of the panles, a lattice structure that replaces longitudinal and transversal stiffeners of the spars and metal panels.
摘要翻译： 所公开的实施例涉及飞机的主要发动机支柱结构，其特征在于，其包括单件复合板，同时替换金属翼梁和金属板，复合板具有沿横向方向定向的纤维层叠， 刨花板的皮肤的宽度，替代翼梁和金属板的纵向和横向加强件的格子结构。
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公开(公告)号：US07503524B2
公开(公告)日：2009-03-17
申请号：US10974537
申请日：2004-10-27
IPC分类号： B64C1/14
CPC分类号： B29C73/10 , B64C1/1446 , B64F5/10
摘要： A removable plate and a flange that occupies a hole in a panel. The flange has the particular feature of taking up compressive force to which the panel is subjected in its plane, perpendicularly to the hole. The weight of the device used to equip the hole is reduced, and the mechanical behavior of the panel at the position of the hole is improved.
摘要翻译： 一个可移动板和一个占用面板孔洞的法兰。 该凸缘具有吸收面板垂直于孔的平面所承受的压缩力的特征。 用于装备孔的装置的重量减小，并且在孔的位置处的面板的机械性能得到改善。
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7.发明申请Method for making a laminated structure and aircraft provided with such a structure 审中-公开制造具有这种结构的层压结构和飞机的方法公开(公告)号：US20050224655A1
公开(公告)日：2005-10-13
申请号：US11001682
申请日：2004-12-01
IPC分类号： B64C1/00 , B64C1/26 , F16B4/00 , F16B5/02 , F16B5/04 , B21K7/00 , B21D53/92 , B21D47/00 , B32B7/08
CPC分类号： F16B5/025 , B64C1/06 , B64C1/12 , B64C1/26 , B64C2001/0072 , B64C2001/0081 , F16B4/004 , F16B5/04 , Y02T50/43 , Y10T29/49622 , Y10T29/49629 , Y10T29/49945 , Y10T29/49947 , Y10T428/24174
摘要： To make a laminated structure comprising a panel made of composite materials and placed flat against at least one metal plate, the panel and the plate are presented in a stack, this stack is drilled to form a fastening borehole, a fastening rod is introduced into the bore and the fastener is fixed. In the invention, during the drilling, a negative clearance is made between a diameter of the bore and a diameter of the fastener, and when the fastener is being introduced, it is introduced from the metal plate. This mode of action prompts a positive interference that promotes the lasting nature of the fastener.
摘要翻译： 为了制造包括由复合材料制成的面板并且平放在至少一个金属板上的面板的层压结构，将面板和板呈堆叠形式，钻出该叠层以形成紧固钻孔，将紧固杆引入 孔和紧固件是固定的。 在本发明中，在钻孔期间，在孔的直径和紧固件的直径之间形成负间隙，并且当紧固件被引入时，其从金属板引入。 这种作用方式提出了积极的干扰，促进了紧固件的持久性。
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