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1. 发明授权

US08567712B2 Fuse link device between a mobile part and a fixed part of an aircraft nacelle 有权
标题翻译：飞机机舱的移动部件和固定部件之间的熔断器连接装置
公开(公告)号：US08567712B2
公开(公告)日：2013-10-29
申请号：US13008592
申请日：2011-01-18
申请人： Alain Porte , Jacques Lalane , Franck Alvarez
发明人： Alain Porte , Jacques Lalane , Franck Alvarez
IPC分类号： B64D29/00 , B64D29/08
CPC分类号： B64D29/06 , B64D29/08
摘要： The object of the invention is an aircraft nacelle that comprises at least one part, called a door (14), that moves relative to a stationary part (20) and a connecting device that makes it possible to limit the offset between said door and said stationary part in a direction that corresponds to the primary direction of the flow of air outside of the nacelle during flight, whereby said device comprises, on the one hand, an indexer (40) that is connected to the door (14) that comprises an attachment surface (63) and at least one attachment element (66), and, on the other hand, at least one stop (58) that is connected to the stationary part (20) against which said indexer (40) can rest in such a way as to limit its movement in said direction, characterized in that said at least one attachment element (66), oriented in the radial direction, is arranged upstream from the stop (58) in said direction, said at least one stop (58) comprising a surface relative to the door arranged essentially at the attachment surface (63) of the indexer (40).
摘要翻译：本发明的目的是一种飞机机舱，其包括称为门（14）的至少一部分，其相对于静止部分（20）和连接装置移动，所述连接装置使得可以限制所述门和所述第二门固定部分在与飞行中的机舱外部的空气流的主要方向对应的方向上，其中所述装置一方面包括连接到门（14）的分度器（40），该分度器包括一个附接表面（63）和至少一个附接元件（66），另一方面，连接到所述固定部分（20）的至少一个止动件（58），所述分度器（40）能够抵靠所述固定部分一种限制其在所述方向上移动的方式，其特征在于，所述至少一个在径向方向上定向的连接元件（66）沿着所述方向设置在止动件（58）的上游，所述至少一个止动件）包括相对于所述门的表面，其基本上a布置 t分度器（40）的附接表面（63）。

2. 发明授权

US07971684B2 Acoustic panel 有权
标题翻译：声学面板
公开(公告)号：US07971684B2
公开(公告)日：2011-07-05
申请号：US12528017
申请日：2008-02-19
申请人： Fabrice Gantie , Bernard Duprieu , Valerie Frustie , Alain Porte , Thomas Gilles , Jacques Lalane
发明人： Fabrice Gantie , Bernard Duprieu , Valerie Frustie , Alain Porte , Thomas Gilles , Jacques Lalane
IPC分类号： E04B1/82
CPC分类号： G10K11/172 , F02C7/24 , F02K1/827 , G10K11/168
摘要： A panel for acoustic treatment connected to a surface of an aircraft, includes—from the outside to the inside—an acoustically resistive porous layer, at least one alveolar structure, and a reflective or impermeable layer, whereby the acoustically resistive porous layer includes—at the outside surface that can be in contact with the aerodynamic flows—one sheet or piece of sheet metal including open zones (14) that allow sound waves to pass and filled zones (16) that do not allow sound waves to pass, characterized in that the sheet or piece of sheet metal of the acoustically resistive layer includes sets of microperforations (18), whereby each set of microperforations forms an open zone (14), the sets of microperforations being separated from one another by at least one series of bands separated by filled zones (16).
摘要翻译：连接到飞行器表面的用于声学处理的面板包括从外部到内部的声阻多孔层，至少一个肺泡结构以及反射或不可渗透层，其中所述声阻多孔层包括可以与气动流动接触的外表面 - 包括允许声波通过并且不允许声波通过的区域（16）的开放区域（14）的一片或片状金属片，其特征在于，阻声层的片状物或片状物包括一组微穿孔（18），由此每组微穿孔形成开放区域（14），所述微穿孔组彼此分开至少一系列带分离通过填充区（16）。

3. 发明申请

US20100276548A1 ACOUSTIC PROCESSING STRUCTURE PARTICULARLY ADAPTED TO THE AIR INLET OF AN AIRCRAFT NACELLE 有权
标题翻译：气动加工结构特别适用于飞机空气入口
公开(公告)号：US20100276548A1
公开(公告)日：2010-11-04
申请号：US12809742
申请日：2008-12-16
申请人： Alain Porte , Jacques Lalane , Fabrice Gantie , Jacques Barillot-Creuzet
发明人： Alain Porte , Jacques Lalane , Fabrice Gantie , Jacques Barillot-Creuzet
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0206 , B64D2033/0233
摘要： An acoustic treatment structure related to a leading edge onto which an aerodynamic stream flows, in particular at an air intake of an aircraft nacelle, includes—from the outside to the inside—at least one acoustically resistive substructure (30), at least one alveolar substructure including strips (32) of cells, arranged in a direction that is essentially perpendicular to the direction of flow of the aerodynamic stream, and at least one reflective layer (34). Each strip (32) includes a first part that insulates the strips from one another, called a support, with a U-shaped cross-section in the longitudinal direction, whose open surface that is opposite to the bottom of the U shape is flattened against the acoustically resistive substructure (30), and at least a second part, called partitioning, making it possible to partition the space that is delimited by the support and the acoustically resistive substructure (30) into cells.
摘要翻译：与空气动力流流动的前缘相关联的声学处理结构，特别是在飞机机舱的空气入口处，包括 - 从外部至内部至少一个声阻子结构（30），至少一个肺泡子结构，包括沿基本上垂直于空气动力流的流动方向布置的细胞条带（32），以及至少一个反射层（34）。每个条带（32）包括第一部分，其将条带彼此绝缘，称为支撑件，其在纵向方向上具有U形横截面，其与U形底部相对的开口表面被平坦化声阻抗子结构（30）和至少第二部分（称为分割），使得可以将由支撑体和声阻子结构（30）限定的空间分隔成单元。

4. 发明授权

US08646723B2 Device for connecting an air inlet with an aircraft nacelle actuator assembly 有权
标题翻译：用于将进气口与飞机机舱致动器组件连接的装置
公开(公告)号：US08646723B2
公开(公告)日：2014-02-11
申请号：US13120025
申请日：2009-09-17
申请人： Alain Porte , Matthieu Fargues , Jacques Lalane
发明人： Alain Porte , Matthieu Fargues , Jacques Lalane
IPC分类号： B64D29/00
CPC分类号： B64D33/02 , B64D29/06 , B64D2033/0206 , B64D2033/0286 , F01D25/243 , F02C7/045
摘要： An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.
摘要翻译：飞机机舱包括进气口，其使得可以沿着布置在管道的延伸部中的发电厂的管道的方向在管道中引导空气，由此进气口的管道包括至少一个面板其将声学处理与与进入机舱的空气动力流接触的声阻性多孔层，至少一个肺泡结构以及形成面板后表面的反射或不可渗透层，确保进气口和发电厂之间的连接包括至少一个通过多个连接元件连接到进气口的机翼，其特征在于，一些连接元件具有与面板边缘相切的轴线，进气管道。

5. 发明申请

US20120048389A1 AIRCRAFT NACELLE INCLUDING AN OPTIMISED ACOUSTIC PROCESSING SYSTEM 有权
标题翻译：包括优化声学处理系统的飞机制造商
公开(公告)号：US20120048389A1
公开(公告)日：2012-03-01
申请号：US13145451
申请日：2010-01-28
申请人： Frédéric Chelin , Alain Porte , Fabrice Gantie , Jacques Lalane
发明人： Frédéric Chelin , Alain Porte , Fabrice Gantie , Jacques Lalane
IPC分类号： F02K99/00
CPC分类号： B64D15/04 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , Y02T50/67 , Y02T50/672 , Y10T137/0536
摘要： An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.
摘要翻译：包括管（32），周壁（34），唇缘（36）和连接周壁（34）和管（32）并且与唇缘（36）形成的前框架（38）的飞机机舱）具有用于霜冻处理的热空气可以循环的空间（50），其中包括用于复合材料声学处理的涂层（44）的管（32）的特征在于，所述机舱包括至少一个元件（52），其由插入在所述唇部（36）和所述管（32）之间的导热材料制成，以确保所述唇部（36）和所述管（32）的空气动力学表面的连续性和来自所述空间（50）朝向所述机舱的后部，由此所述至少一个元件（52）包括由耐热材料制成的用于声学处理的涂层（54）。

6. 发明授权

US09284060B2 Aircraft nacelle including a rear frame inclined to the rear 有权
标题翻译：飞机机舱包括一个向后倾斜的后框架
公开(公告)号：US09284060B2
公开(公告)日：2016-03-15
申请号：US13270536
申请日：2011-10-11
申请人： Alain Porte , Jacques Lalane , Frederic Chelin
发明人： Alain Porte , Jacques Lalane , Frederic Chelin
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/0206 , B64D2033/0286 , Y10T137/0536
摘要： An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.
摘要翻译：飞机机舱包括其表面与空气动力流接触的唇缘，其通过内壁在内部壁延伸，所述内壁限定通过外壁在发电厂和机舱外部排空的层，第一前框架连接内外围绕边缘限定一个环形管，并且后框架在内管和发电厂管之间的接合区连接内壁和外壁，对于机舱的给定横截面沿着包含纵向轴线的平面机舱，后框架和内壁之间的交点处的点A和后框架与外壁之间的交叉点处的点B，其中B相对于A更靠近机舱的后部超过后框架周边的50％。

7. 发明授权

US08602346B2 Acoustic treatment panel with integral connecting reinforcement 有权
标题翻译：声学处理板与集成连接加强件
公开(公告)号：US08602346B2
公开(公告)日：2013-12-10
申请号：US12937445
申请日：2009-04-07
申请人： Alain Porte , Jacques Lalane
发明人： Alain Porte , Jacques Lalane
IPC分类号： B64C1/40
CPC分类号： B64D33/02 , B64D2033/0206
摘要： An acoustic treatment panel includes, from the inside to the outside, a reflective layer (50), at least one alveolar structure (52), and at least one acoustically resistive structure (54) that forms an aerodynamic surface, whereby the panel is connected at one edge to at least one second panel (46), characterized in that it includes, at the edge overlapping with the at least one second panel, a reinforcement (60) that is inserted between the reflective layer (50) and the acoustically resistive structure (54) forming the aerodynamic surface, whereby the reinforcement (60) ensures the uptake of forces between the layer (50) and the structure (54).
摘要翻译：声处理面板包括从内到外的反射层（50），至少一个肺泡结构（52）和至少一个形成空气动力学表面的声阻结构（54），由此面板连接在一个边缘处至少一个第二面板（46），其特征在于，其在与所述至少一个第二面板重叠的边缘处包括加强件（60），其被插入在所述反射层（50）和所述声阻结构（54）形成空气动力学表面，由此加强件（60）确保层（50）和结构（54）之间的力的吸收。

8. 发明申请

US20120261521A1 NACELLE INCORPORATING AN ELEMENT FOR CONNECTING A LIP AND AN ACOUSTIC ATTENUATION PANEL TOGETHER 有权
标题翻译：连接一个LIP和一个声音衰减面板的元件的NACELLE
公开(公告)号：US20120261521A1
公开(公告)日：2012-10-18
申请号：US13518041
申请日：2010-12-21
申请人： Alain Porte , Jacques Lalane
发明人： Alain Porte , Jacques Lalane
IPC分类号： B64C7/02
CPC分类号： B64D33/02 , B64C7/02 , B64D29/00 , B64D29/06 , B64D2033/0206
摘要： An aircraft nacelle includes a first subassembly consisting of a pipe (112) channeling an airflow in the direction of an engine having a covering or panel (118) for acoustic treatment, including, from the inside to the outside, a reflecting layer (120), at least one cellular structure (122), and at least one acoustically resistive structure (124) forming the aerodynamic surface of the pipe (112), as well as a second subassembly consisting of a lip (116) and a front frame (126), characterized in that it includes at least one connection element (134) which is separate from the two subassemblies and connected to a portion of the pipe (112) and to a portion of the lip forming an extension of the portion of the pipe at different points so as to be capable of enabling a relative movement between the two subassemblies.
摘要翻译：一种飞机机舱包括一个第一子组件，该组件包括一个管道（112），该管道（112）引导具有用于声学处理的覆盖物或面板（118）的发动机的方向上的气流，包括从内到外的反射层（120），至少一个蜂窝结构（122）和形成管（112）的空气动力学表面的至少一个声阻结构（124），以及由唇部（116）和前框架（126）组成的第二子组件），其特征在于，其包括至少一个连接元件（134），其与两个子组件分离并连接到管道（112）的一部分，并且与唇部的一部分形成管的该部分的延伸部分以便能够实现两个子组件之间的相对移动。

9. 发明申请

US20100199629A1 SYSTEME D'ANTI GIVRAGE ET DE DEGIVRAGE DE NACELLE DE MOTEUR D'AERONEF A TAPIS RESISTIF 审中-公开
标题翻译：系统D'ANTI GIVRAGE ET DE DEIVRAGE DE NACELLE DE MOTEUR D'AERONEF A TAPIS RESISTIF
公开(公告)号：US20100199629A1
公开(公告)日：2010-08-12
申请号：US11993693
申请日：2006-06-19
申请人： Gilles Chene , Alain Porte , Jacques Lalane
发明人： Gilles Chene , Alain Porte , Jacques Lalane
IPC分类号： B64D15/12 , F02G3/00
CPC分类号： B64D15/12 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/047 , F05D2250/132 , Y02T50/672
摘要： A deicing and anti-icing system for an aircraft engine pod, including an air intake provided with a lip followed by an air intake tubular part, equipped with a first sound attenuating panel, including deicing means having at least one array of resistive heating elements embedded in an insulating material, the deicing means being in the form of a mat incorporating the resistive element in the thickness of the air intake lip.
摘要翻译：一种用于飞机发动机舱的除冰和防冰系统，包括设置有唇部的进气口以及进气管状部件，该空气入口装备有第一声音衰减面板，其包括除冰装置，该除冰装置具有嵌入的至少一个电阻加热元件阵列在绝缘材料中，除冰装置是在吸气唇的厚度中包含电阻元件的垫的形式。

10. 发明申请

US20100116587A1 ACOUSTIC PANEL 有权
标题翻译：声学面板
公开(公告)号：US20100116587A1
公开(公告)日：2010-05-13
申请号：US12528017
申请日：2008-02-19
申请人： Fabrice Gantie , Bernard Duprieu , Valerie Frustie , Alain Porte , Thomas Gilles , Jacques Lalane
发明人： Fabrice Gantie , Bernard Duprieu , Valerie Frustie , Alain Porte , Thomas Gilles , Jacques Lalane
IPC分类号： E04B1/82
CPC分类号： G10K11/172 , F02C7/24 , F02K1/827 , G10K11/168
摘要： The invention relates to a panel for an acoustic treatment at the surface of an aircraft, that comprises from the outside to the inside an acoustically resistive porous layer, at least one cellular structure and a reflective or non-permissive layer, wherein the acoustically resistive porous layer includes, at the outer surface that may contact the aerodynamic flows of a sheet or foil, open areas (14) permissive to sound waves and solid area (6) not permissive to sound waves, characterised in that the sheet or foil of the acoustically resistive layer includes sets of microperforations (18), each set of microperforations defining an open area (14), the set of microperforations being separated by at least one series of spaced bands of solid areas (16).
摘要翻译：本发明涉及一种用于在飞行器表面处进行声学处理的面板，其包括从外部到内部的声阻多孔层，至少一个蜂窝结构和反射或非允许层，其中所述声阻多孔在可能接触片材或箔片的空气动力学流动的外表面处包括允许声波的开放区域（14）和不允许声波的固体区域（6），其特征在于，声学的片材或箔片电阻层包括一组微穿孔（18），每套微穿孔限定开放区域（14），所述一组微穿孔由至少一系列间隔的固体区域（16）分隔开。

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