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11. 发明授权

US08220154B2 Method for fabricating an aircraft fuselage in composite material 有权
标题翻译：复合材料制造飞机机身的方法
公开(公告)号：US08220154B2
公开(公告)日：2012-07-17
申请号：US12158214
申请日：2006-12-19
申请人： Bruno Cacciaguerra
发明人： Bruno Cacciaguerra
IPC分类号： B21D53/88
CPC分类号： B64C1/068 , B29C70/32 , B29C70/86 , B29L2031/3082 , B64C1/061 , B64C1/064 , B64C1/12 , B64C2001/0072 , B64F5/10 , Y02T50/43 , Y10T29/49622
摘要： A method for manufacturing an aircraft fuselage includes an internal framework surrounded by an external skin made of composite material, in which the internal framework at least partially constitutes a mould for manufacture and/or the support for the mould for the external skin made of composite material. The disclosed embodiments also relate to an aircraft fuselage produced using this method.
摘要翻译：一种用于制造飞机机身的方法包括由复合材料制成的外部皮肤包围的内部框架，其中内部框架至少部分地构成用于制造的模具和/或用于由复合材料制成的外部皮肤的模具的支撑。所公开的实施例还涉及使用该方法产生的飞行器机身。

12. 发明授权

US07963477B2 Aircraft that comprises a structure that ensures the structural and electrical functions 有权
标题翻译：包括确保结构和电气功能的结构的飞机
公开(公告)号：US07963477B2
公开(公告)日：2011-06-21
申请号：US12062791
申请日：2008-04-04
申请人： Denis Soula , Bruno Cacciaguerra , Alain Tropis , Nicolas Alglave
发明人： Denis Soula , Bruno Cacciaguerra , Alain Tropis , Nicolas Alglave
IPC分类号： B64D45/00
CPC分类号： B64C1/061 , B64C2001/0072 , B64C2001/0081 , B64D45/02 , Y02T50/43
摘要： An aircraft includes a structure with structural elements (16) that are assembled to form a three-dimensional framework to which an aerodynamic envelope (14) is attached. At least some structural elements (16) are at least partly metallic and—at the connection with the aerodynamic envelope (14)—including an interface that is made of material that has a conductivity that is below a threshold on the order of 10,000 S/m so as to form at least one electrical path that ensures the functions of electric return and metallization of the electrical systems, whereby connections that ensure the electrical conduction are provided between the structural elements (16).
摘要翻译：飞机包括具有结构元件（16）的结构，其被组装以形成附接有空气动力学外壳（14）的三维框架。至少一些结构元件（16）至少部分地是金属的，并且在与空气动力学外壳（14）的连接处 - 包括由导电率低于约10,000 S / cm 2的阈值的材料制成的界面，以便形成确保电气系统的电返回和金属化的功能的至少一个电路径，由此在结构元件（16）之间提供确保电传导的连接。

13. 发明申请

US20100264272A1 AIRCRAFT STRUCTURE INCLUDING STIFFENER EDGE JUNCTIONS 有权
标题翻译：飞机结构包括加速器边缘接头
公开(公告)号：US20100264272A1
公开(公告)日：2010-10-21
申请号：US12738600
申请日：2008-09-12
申请人： Helene Cazeneuve , Bruno Cacciaguerra , Jean-Claude Lacombe , David Andissac
发明人： Helene Cazeneuve , Bruno Cacciaguerra , Jean-Claude Lacombe , David Andissac
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。

14. 发明申请

US20080251636A1 AIRCRAFT THAT COMPRISES A STRUCTURE THAT ENSURES THE STRUCTURAL AND ELECTRICAL FUNCTIONS 有权
标题翻译：包含结构和电气功能的结构的飞机
公开(公告)号：US20080251636A1
公开(公告)日：2008-10-16
申请号：US12062791
申请日：2008-04-04
申请人： Denis Soula , Bruno Cacciaguerra , Alain Tropis , Nicolas Alglave
发明人： Denis Soula , Bruno Cacciaguerra , Alain Tropis , Nicolas Alglave
IPC分类号： B64D45/02
CPC分类号： B64C1/061 , B64C2001/0072 , B64C2001/0081 , B64D45/02 , Y02T50/43
摘要： An aircraft includes a structure with structural elements (16) that are assembled to form a three-dimensional framework to which an aerodynamic envelope (14) is attached. At least some structural elements (16) are at least partly metallic and—at the connection with the aerodynamic envelope (14)—including an interface that is made of material that has a conductivity that is below a threshold on the order of 10,000 S/m so as to form at least one electrical path that ensures the functions of electric return and metallization of the electrical systems, whereby connections that ensure the electrical conduction are provided between the structural elements (16).
摘要翻译：飞机包括具有结构元件（16）的结构，其被组装以形成附接有空气动力学外壳（14）的三维框架。至少一些结构元件（16）至少部分地是金属的，并且在与空气动力学外壳（14）的连接处 - 包括由导电率低于约10,000 S / cm 2的阈值的材料制成的界面，以便形成确保电气系统的电返回和金属化的功能的至少一个电路径，由此在结构元件（16）之间提供确保电传导的连接。

15. 发明授权

US5971443A Threaded joint for pipes 失效
标题翻译：螺纹接头用于管道
公开(公告)号：US5971443A
公开(公告)日：1999-10-26
申请号：US49016
申请日：1998-03-27
申请人： Thierry Noel , Bruno Cacciaguerra
发明人： Thierry Noel , Bruno Cacciaguerra
IPC分类号： E21B17/042 , E21B17/043 , F16L15/04 , F16L15/08 , F16L7/00 , F16B39/00 , F16L9/00
CPC分类号： F16L15/004 , E21B17/043 , E21B17/085 , F16L15/009 , F16L15/08 , Y10S285/915
摘要： The invention pertains to a tubular threaded joint provided with a device opposed to over-screwing or unscrewing. The joint includes a male component (3) with an external threading (8) and a female component (2) with internal threading (6), these two components capable of being assembled with predetermined amount of torque. A female portion (7) arranged beyond the female threading (19) and a male portion (13) arranged beyond the male threading (12) provide between their internal surface (14) and external surface (15) an annular zone in which one part at least forms a calibrated zone (20) in which an adhesive ensures mechanical connection between the female portion (7) and the male portion (13). Use of the joint particularly for the oil and gas industry.
摘要翻译：本发明涉及一种管状螺纹接头，该螺纹接头设置有与过度拧紧或旋松相对的装置。接头包括具有外螺纹（8）的阳部件（3）和具有内螺纹（6）的阴部件（2），这两个部件能够以预定量的扭矩组装。布置在阴螺纹（19）之外的阴部分（7）和布置在阳螺纹（12）之外的阳部分（13）在其内表面（14）和外表面（15）之间提供环形区域，其中一个部分至少形成校准区域（20），其中粘合剂确保阴部分（7）和阳部分（13）之间的机械连接。特别用于油气工业的联合使用。

16. 发明授权

US08215584B2 Aircraft structure including stiffener edge junctions 有权
标题翻译：飞机结构包括加强筋边缘接头
公开(公告)号：US08215584B2
公开(公告)日：2012-07-10
申请号：US12738600
申请日：2008-09-12
申请人： Helene Cazeneuve , Bruno Cacciaguerra , Jean-Claude Lacombe , David Andissac
发明人： Helene Cazeneuve , Bruno Cacciaguerra , Jean-Claude Lacombe , David Andissac
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。

17. 发明授权

US08083182B2 Monolithic self-stiffened panels 有权
标题翻译：单片自加强板
公开(公告)号：US08083182B2
公开(公告)日：2011-12-27
申请号：US11996302
申请日：2006-07-12
申请人： Bruno Cacciaguerra
发明人： Bruno Cacciaguerra
IPC分类号： B64C1/14
CPC分类号： B64C25/16 , B64C1/12 , B64C2001/0072 , B64C2001/0081 , Y02T50/43
摘要： A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).
摘要翻译：一种复合面板，其具有形成面板外壁的第一皮肤，称为下表面（1），以及形成面板内壁部分的第二皮肤。第二皮肤形成为中空的，以产生半框结构（3）形式的内部加强框架（2），其与第一皮肤一起形成箱体部件。上述框架配备有用于固定到第一皮肤的边缘（4a，4b），称为上表面（5）的表面和连接侧壁（6,6a，6b，6c，6d，6e，7）之间的边缘边缘（4a，4b）和上表面（5），第一和第二表皮形成一体的自加强板。半框框架（2）具有由形成半框框架（2）的中空梁部分限定的穿孔部分（8）。

18. 发明授权

US07942369B2 Windscreen frame and a method of production for a windscreen frame 有权
标题翻译：挡风玻璃框架和挡风玻璃框架的生产方法
公开(公告)号：US07942369B2
公开(公告)日：2011-05-17
申请号：US11854677
申请日：2007-09-13
申请人： Benjamin Mahieu , Bruno Cacciaguerra , Louis Peltier
发明人： Benjamin Mahieu , Bruno Cacciaguerra , Louis Peltier
IPC分类号： B64C1/14
CPC分类号： B64C1/1476 , Y02T50/43
摘要： A windscreen frame, and a method of production for a windscreen frame, designed to hold a windscreen in an opening in a wall, the frame including at least one upper horizontal frame section element, at least one lower horizontal frame section element and at least one vertical mounting, characterized in that it is a single unit in composite material.
摘要翻译：一种挡风玻璃框架和用于挡风玻璃框架的生产方法，其被设计成将挡风玻璃保持在壁的开口中，所述框架包括至少一个上部水平框架部分元件，至少一个下部水平框架部分元件和至少一个垂直安装，其特征在于它是复合材料中的单个单元。

19. 发明授权

US07874516B2 Structural frame for an aircraft fuselage 有权
标题翻译：机身结构框架
公开(公告)号：US07874516B2
公开(公告)日：2011-01-25
申请号：US11718845
申请日：2005-11-07
申请人： Bruno Cacciaguerra
发明人： Bruno Cacciaguerra
IPC分类号： B64C1/00
CPC分类号： B64C1/18 , B64C1/061 , B64C1/062 , B64C2001/0072 , B64C2001/0081 , Y02T50/43
摘要： A structural frame for a fuselage including a lower arched structure (1), a cross-piece (2), supporting a floor element (3) and a connecting lattice (4) between the lower arch (1) and the cross-piece (2), the connecting lattice (4) more particularly may comprise bars (4a, 4b) the ends of which are spliced to the cross-piece (2) and the lower arch (1).
摘要翻译：一种用于机身的结构框架，包括下弓形结构（1），横梁（2），支撑地板元件（3）和下弓（1）与横梁（1）之间的连接格（4）更具体地说，连接格子（4）可以包括杆（4a，4b），杆的端部被接合到横梁（2）和下弓（1）。

20. 发明申请

US20100282905A1 SPLICING OF OMEGA-SHAPED STIFFENERS AT A CIRCUMFERENTIAL JOINT IN AN AIRCRAFT FUSELAGE 有权
标题翻译：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
申请人： Helene Cazeneuve , Bruno Cacciaguerra
发明人： Helene Cazeneuve , Bruno Cacciaguerra
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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