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公开(公告)号：US20100264272A1
公开(公告)日：2010-10-21
申请号：US12738600
申请日：2008-09-12
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/43
摘要： An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.
摘要翻译： 一种飞机结构，包括在接合处组装的加强板，不加强筋的连续性。 多个面板用于形成飞机的机身，尾翼和机翼。 这些面板包括在每个面板连接处中断的加强件。 然而，尽管有这些中断，加强件经受的应力必须被传送。 已知的解决方案需要使用每个加强筋至少一个附加部件和每个中断。 为了解决这个问题，所公开的实施例包括对于该区域中的所有被中断的加强件，每个面板接合面积最多需要一个附加部件的倍增器。
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公开(公告)号：US08215584B2
公开(公告)日：2012-07-10
申请号：US12738600
申请日：2008-09-12
IPC分类号： B64C1/06
CPC分类号： B64C1/064 , B64C1/069 , B64C2001/0072 , Y02T50/43
摘要： An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.
摘要翻译： 一种飞机结构，包括在接合处组装的加强板，不加强筋的连续性。 多个面板用于形成飞机的机身，尾翼和机翼。 这些面板包括在每个面板连接处中断的加强件。 然而，尽管有这些中断，加强件经受的应力必须被传送。 已知的解决方案需要使用每个加强筋至少一个附加部件和每个中断。 为了解决这个问题，所公开的实施例包括对于该区域中的所有被中断的加强件，每个面板接合面积最多需要一个附加部件的倍增器。
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公开(公告)号：US20130181092A1
公开(公告)日：2013-07-18
申请号：US13533266
申请日：2012-06-26
申请人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Helene Cazeneuve , Marc-Antoine Castanet
发明人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Helene Cazeneuve , Marc-Antoine Castanet
CPC分类号： B64C1/069 , B64C1/068 , B64C2001/0081 , B64F5/10 , Y10T29/49622
摘要： Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.Set of fuselage sections assembled by means of a device of the type described above.Method of assembling two fuselage sections by means of a device of the type described above.
摘要翻译： 用于组装两个飞行器机身部分的装置，每个飞行器机身部分各自包括皮肤和纵向加强件，该装置包括分别属于所述部分的相互对齐的纵向加强件的鱼板钓鱼钩，每个鱼板包括两个鱼板块，每个鱼板包括至少一个用于固定的纵向底板 纵向加强件和横向支撑头以及能够相互夹紧所述鱼板片的相应支撑头的至少一个可拆卸连接件，以允许在这些鱼片之间传递纵向力。 通过上述类型的装置组装的机身部分组。 通过上述类型的装置组装两个机身部分的方法。
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4.发明授权Splicing of omega-shaped stiffeners at a circumferential joint in an aircraft fuselage 有权在飞机机身的圆周接头处接合Ω形加强件公开(公告)号：US08302909B2
公开(公告)日：2012-11-06
申请号：US12738594
申请日：2008-10-15
IPC分类号： B64C1/00
CPC分类号： B64C1/06 , B64C1/069 , B64C2001/0072 , Y02T50/43
摘要： An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.
摘要翻译： 通过在周向接头处组装至少两个部分，每个部分包括涂层和至少一个加强件的至少一个元件而制造的飞行器机身，上述两个元件具有闭合的横截面并且由拼接件组装。 加强件和拼接件的元件由复合材料制成。 具有两个凸缘的上述拼接片通过仅位于上述拼接件的凸缘上的工作紧固件固定到涂层和加强件上。
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5.发明申请SPLICING OF OMEGA-SHAPED STIFFENERS AT A CIRCUMFERENTIAL JOINT IN AN AIRCRAFT FUSELAGE 有权在航空器熔断器中的圆形接头处的欧米茄型强化器的分离公开(公告)号：US20100282905A1
公开(公告)日：2010-11-11
申请号：US12738594
申请日：2008-10-15
IPC分类号： B64C1/12
CPC分类号： B64C1/06 , B64C1/069 , B64C2001/0072 , Y02T50/43
摘要： An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.
摘要翻译： 通过在周向接头处组装至少两个部分，每个部分包括涂层和至少一个加强件的至少一个元件而制造的飞行器机身，上述两个元件具有闭合的横截面并且由拼接件组装。 加强件和拼接件的元件由复合材料制成。 具有两个凸缘的上述拼接片通过仅位于上述拼接件的凸缘上的工作紧固件固定到涂层和加强件上。
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