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1. 发明授权

US10150553B2 Device and method for assembling two sections of aircraft fuselage 有权
公开(公告)号：US10150553B2
公开(公告)日：2018-12-11
申请号：US13533266
申请日：2012-06-26
申请人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Hélène Cazeneuve , Marc-Antoine Castanet
发明人： Bruno Cacciaguerra , Alain Depeige , Jean-Claude Lacombe , Hélène Cazeneuve , Marc-Antoine Castanet
IPC分类号： B64C1/06 , B64F5/10 , B64C1/00
摘要： A device and method 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.

2. 发明申请

US20130181092A1 DEVICE AND METHOD FOR ASSEMBLING TWO SECTIONS OF AIRCRAFT FUSELAGE 审中-公开
标题翻译：用于组装飞机熔接两段的装置和方法
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
IPC分类号： B64C1/06 , B64F5/00
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。

3. 发明申请

US20120193472A1 STAIRWAY FOR AN AIRCRAFT 审中-公开
标题翻译：空中客车
公开(公告)号：US20120193472A1
公开(公告)日：2012-08-02
申请号：US13444591
申请日：2012-04-11
申请人： Bernard GUERING , Jonathan GUERING
发明人： Bernard GUERING , Jonathan GUERING
IPC分类号： B64D11/00 , B64D45/00 , B64C1/14
CPC分类号： B64D11/00 , B64D2011/0076
摘要： A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position.
摘要翻译：用于从理论上水平的较低水平到理论上水平的较高水平的梯级，并包括这两个层次之间的一系列中间步骤。对应于最靠近下层的台阶的中间步骤的子组件在第一展开位置之间是可移动的，第一展开位置处下部中间台阶处于其它中间台阶的延伸部分中，并且升高位置使下部中间台阶基本上垂直位置。

4. 发明授权

US08226029B2 Engine mounting structure for aircraft with a rear engine attachment beam forming a spreader beam 有权
标题翻译：具有后发动机附件梁的飞机的发动机安装结构，形成吊架梁
公开(公告)号：US08226029B2
公开(公告)日：2012-07-24
申请号：US12663430
申请日：2008-06-19
申请人： Eric Haramburu , Laurent Sammito , Jean Larrochelle
发明人： Eric Haramburu , Laurent Sammito , Jean Larrochelle
IPC分类号： B64D27/00
CPC分类号： B64D27/26
摘要： An engine mounting structure for an engine aircraft including a rigid structure forming a caisson, together with an engine mounting system mounted on the structure, and a rear engine attachment, including an attachment strut to which is connected at least one shackle, to be connected to the engine. The engine mounting system includes a system for transmitting thrust efforts generated by the engine, including two lateral connecting rods connected to a spreader beam mounted in articulated fashion relative to the caisson. The attachment strut constitutes the spreader beam, wherein the body is mounted in articulated fashion relative to the caisson using an articulated shaft system.
摘要翻译：一种用于发动机飞机的发动机安装结构，包括形成沉箱的刚性结构，以及安装在结构上的发动机安装系统，以及包括附接支柱的后部发动机附件，连接至少一个卸扣，连接至至少一个卸扣引擎。发动机安装系统包括用于传递由发动机产生的推力的系统，该系统包括连接到相对于沉箱以铰接方式安装的吊架梁的两个横向连接杆。附件支柱构成吊具梁，其中主体使用铰接轴系相对于沉箱以铰接方式安装。

5. 发明授权

US08226027B2 Engine assembly for aircraft with sliding nacelle 有权
标题翻译：具有滑动机舱的飞机发动机总成
公开(公告)号：US08226027B2
公开(公告)日：2012-07-24
申请号：US12601355
申请日：2008-05-30
申请人： Frederic Journade , Laurent Lafont
发明人： Frederic Journade , Laurent Lafont
IPC分类号： B64D27/00 , B64D29/06
CPC分类号： B64D29/08 , B64D33/04 , F02C7/20 , F02K1/72 , F05D2250/41 , F05D2260/96 , Y02T50/671
摘要： An aircraft engine assembly including a turbojet, a turbojet attachment pylon, and a nacelle mounted on the attachment pylon and surrounding the turbojet. The nacelle includes at least one mobile nacelle portion forming a single piece envelope all around a section of the turbojet, this mobile nacelle portion being mounted free to slide on the attachment pylon so that it can be moved from the forward position in the aft direction, and vice versa.
摘要翻译：包括涡轮喷气发动机，涡轮喷气发动机附件塔和安装在附件塔上并围绕涡轮喷气发动机的机舱的飞机发动机组件。机舱包括至少一个在涡轮喷气发动机的整个部分周围形成单件包封的移动机舱部分，该移动机舱部分可自由地安装在附接塔架上滑动，使得其可以在向后方向上从前部位置移动，反之亦然。

6. 发明申请

US20100287776A1 METHOD FOR ASSEMBLING A PART OF A METAL MATERIAL AND A PART OF A COMPOSITE MATERIAL USING A FASTENER 有权
标题翻译：使用紧固件组装金属材料的一部分和复合材料的一部分的方法
公开(公告)号：US20100287776A1
公开(公告)日：2010-11-18
申请号：US12598005
申请日：2008-05-06
申请人： Nicolas Dantou , Stephane Bianco , Christian Godenzi
发明人： Nicolas Dantou , Stephane Bianco , Christian Godenzi
IPC分类号： B23P19/04 , B23P9/00 , B21D53/92
CPC分类号： B23P9/00 , B21J15/147 , B23P9/025 , B23P19/06 , B23P2700/01 , B29C65/562 , B29C66/45 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/742 , B29K2305/00 , C21D7/02 , F16B5/02 , Y10T29/47 , Y10T29/49 , Y10T29/49622 , Y10T29/49954 , Y10T29/49956 , Y10T29/5377 , Y10T403/4966 , Y10T403/75 , B29K2307/04 , B29K2063/00
摘要： A method for assembling a part of a metal material and a part of a composite material, the junction of the two parts being achieved through a fastener having a substantially constant section and received in a first hole formed in the part of a metal material and a second hole formed in the part of a composite material. According to the disclosed embodiments and before assembling the aforementioned parts, the method includes: an expansion step for generating a field of compression stresses at the periphery of the first hole and locally in the material constituting the part of a metal material using an expansion tool; a single boring step for making the first hole and the second hole with a diameter Øfinal substantially larger than the diameter of the fastener in order to leave a gap between the inner walls of the holes and the outer surface of the fastener; and an assembling step for placing the fastener inside the holes for maintaining together the metal part and the composite part.
摘要翻译：一种用于组装金属材料的一部分和复合材料的一部分的方法，两部分的接合通过具有基本上恒定的部分的紧固件实现，并被接纳在形成在金属材料部分中的第一孔中，并且第二孔形成在复合材料的一部分中。根据所公开的实施例，在组装上述部件之前，该方法包括：膨胀步骤，用于在第一孔的周边处产生压缩应力场，并局部地使用膨胀工具构成金属材料的部分; 用于制造第一孔和第二孔的单个镗孔步骤，其直径直径基本上大于紧固件的直径，以便在孔的内壁和紧固件的外表面之间留下间隙; 以及用于将紧固件放置在用于将金属部件和复合部件保持在一起的孔内的组装步骤。

7. 发明申请

US20100268517A1 METHOD AND TOOL FOR SIMULATION OF THE AERODYNAMIC BEHAVIOUR OF AN AIRCRAFT IN FLIGHT CLOSE TO THE GROUND 有权
标题翻译：模拟飞机上靠近地面的飞机的航空行为的方法和工具
公开(公告)号：US20100268517A1
公开(公告)日：2010-10-21
申请号：US12759138
申请日：2010-04-13
申请人： Benoit CALMELS
发明人： Benoit CALMELS
IPC分类号： G06F7/60 , G06F17/10
CPC分类号： G06F17/5018 , G06F17/5095 , G06F2217/16
摘要： The invention relates to a method of computer simulation of the aerodynamic behaviour of an aircraft (10) in flight close to the ground. This method is used to identify the slope effect relative to the ground effect.To achieve this, a uniform boundary condition comprising a predetermined speed (UP) with a non-zero tangential component and a non-zero normal component is imposed on a plane (21) modelling the ground; and a discrete numerical model of the Navier-Stokes equations is solved by computer on a volume mesh with said boundary condition imposed on said plane (21), so as to obtain a numerical solution for a fluid flow inside a computational domain defined by said mesh.
摘要翻译：本发明涉及一种计算机模拟飞行器（10）在飞行中靠近地面的空气动力学行为的方法。该方法用于识别相对于地面效应的斜率效应。为了实现这一点，在对地面建模的平面（21）上施加包括具有非零切向分量和非零正态分量的预定速度（UP）的均匀边界条件; 并且通过计算机在具有施加在所述平面（21）上的所述边界条件的体积网格上解决Navier-Stokes方程的离散数值模型，以便获得由所述网格定义的计算域内的流体流动的数值解。

8. 发明申请

US20100215499A1 BLADE RETAINING DEVICE FOR TURBO MACHINE PROPELLER 有权
标题翻译：涡轮机螺旋桨叶片保持装置
公开(公告)号：US20100215499A1
公开(公告)日：2010-08-26
申请号：US12709793
申请日：2010-02-22
申请人： Laurent LAFONT
发明人： Laurent LAFONT
IPC分类号： F01D5/30
CPC分类号： F02K3/025 , B64C11/06 , F01D5/147 , F01D5/30 , F01D7/00 , F01D21/045 , F02K3/062 , F04D29/34 , F05D2260/30 , F05D2260/74 , F05D2260/79 , Y02T50/66 , Y02T50/673
摘要： The invention concerns an aircraft turbomachine propeller comprising a plurality of blades (1) each comprising a root (20) mounted on a hub (2) rotating about the rotation axis of the propeller (I-I), and its purpose is to reduce the risks of loss of the entire blade (1) following an impact by a foreign body.To achieve this, at least one blade (1) comprises a means (30) of retaining the blade in an outwards radial direction, said retaining means (30) being engaged in a housing (5) of said blade (1) opening radially inwards at the root of the blade (20), and fixed in translation in said outwards radial direction.
摘要翻译：本发明涉及一种包括多个叶片（1）的飞机涡轮机推进器，每个叶片包括安装在围绕螺旋桨（II）的旋转轴线旋转的轮毂（2）上的根部（20），并且其目的是降低整个叶片（1）在异物撞击后的损失。为了实现这一点，至少一个叶片（1）包括将叶片保持在向外径向的装置（30），所述保持装置（30）接合在所述叶片（1）的径向向内开口的壳体（5）中在叶片（20）的根部处，并且以所述向外的径向方向固定成平移。

9. 发明申请

US20100170999A1 MORE ELECTRIC FLIGHT CONTROL SYSTEM ONBOARD AN AIRCRAFT 有权
标题翻译：更多电动飞行控制系统
公开(公告)号：US20100170999A1
公开(公告)日：2010-07-08
申请号：US12651603
申请日：2010-01-04
申请人： Marc FERVEL , Alexandre Gentilhomme
发明人： Marc FERVEL , Alexandre Gentilhomme
IPC分类号： B64C13/40
CPC分类号： B64C13/00 , B64C13/50 , B64C13/504 , Y02T50/54
摘要： The invention relates to a more electric flight control system onboard an aircraft provided with flight control surfaces and means of controlling these surfaces, that comprises at least one local electro-hydraulic generator (HPP1, HPP2) to supply hydraulic servocontrols (34) connected to flight control surfaces (31, 32, 33).
摘要翻译：本发明涉及一种具有飞行控制表面的飞行器上的更多电动飞行控制系统和控制这些表面的装置，该飞行控制系统包括至少一个局部电液发生器（HPP1，HPP2），以提供连接到飞行的液压伺服控制装置控制表面（31,32,33）。

10. 发明申请

US20100132378A1 HYDRAULIC SYSTEM FOR TRANSMISSION OF FORCES BETWEEN AN AIRCRAFT TURBOPROP AND AN ATTACHMENT DEVICE 有权
标题翻译：液压系统，用于在航空器涡轮机和附件装置之间传输力
公开(公告)号：US20100132378A1
公开(公告)日：2010-06-03
申请号：US12623777
申请日：2009-11-23
申请人： Jacques Hervé MARCHE
发明人： Jacques Hervé MARCHE
IPC分类号： F02C7/20 , F16M13/00
CPC分类号： B64D27/12
摘要： This invention relates to a force transmission system (50) between a turboprop and an attachment pylon, comprising: a first and a second force transmission device (52a, 52b) each comprising a first hollow cylinder (54) with an axis (56) that will be made parallel to a first force transmission direction, said first cylinder defining a first space (58) full of a fluid (60) and closed off in a sealed manner at its two opposite ends, by a first damping layer (62) that will bear in contact with a bearing element (66) of the turboprop, and by a second damping layer (64) that will bear in contact with a bearing element (68) of the attachment device, said first and second layers possibly being compressed by the pressure of said fluid; and first means (70) of fluid communication between the two spaces (58, 58).
摘要翻译：技术领域本发明涉及一种在涡轮螺旋桨和附件塔之间的力传递系统（50），包括：第一和第二力传递装置（52a，52b），每个包括具有轴线（56）的第一中空圆柱体（54）将平行于第一力传递方向制成，所述第一气缸限定充满流体（60）的第一空间（58），并且通过第一阻尼层（62）在其两个相对端以密封方式封闭，所述第一阻尼层将承受与涡轮螺旋桨发动机的轴承元件（66）接触，以及与承载元件（68）接触的第二阻尼层（64），所述第一和第二层可能被所述流体的压力; 以及在两个空间（58,58）之间流体连通的第一装置（70）。

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