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1. 发明授权

US09003760B2 Acoustic processing panel, more particularly adapted for an air intake in an aircraft nacelle 有权
标题翻译：声学处理面板，更特别适用于飞机机舱中的进气口
公开(公告)号：US09003760B2
公开(公告)日：2015-04-14
申请号：US13145685
申请日：2010-01-29
申请人： Frédéric Chelin , Thierry Surply , Dominique Haro , Fabrice Gantie , David Lambert
发明人： Frédéric Chelin , Thierry Surply , Dominique Haro , Fabrice Gantie , David Lambert
IPC分类号： B64D15/04 , F02C7/047 , F02C7/045 , B64D33/02 , F02K1/82
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/047 , F02K1/827 , Y10T137/0536
摘要： An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.
摘要翻译：连接到飞机机舱的进气口的声学处理面板包括至少一个声阻构造（30）和反射层（32），它们位于基本垂直于纵向方向的方向上（34）的肺泡细胞间隔开以允许用于霜冻治疗的热空气的通过，其特征在于，其包括用于热空气的管（36），每个管（36）分别由至少一个隔板从隔音层（30）延伸到反射层（32），以使得单元的带（34）在纵向方向上绝缘。

2. 发明申请

US20120090693A1 ACOUSTIC PROCESSING PANEL, MORE PARTICULARLY ADAPTED FOR AN AIR INTAKE IN AN AIRCRAFT NACELLE 有权
标题翻译：声音处理面板，更特别适用于飞机上的空气入口
公开(公告)号：US20120090693A1
公开(公告)日：2012-04-19
申请号：US13145685
申请日：2010-01-29
申请人： Frédéric Chelin , Thierry Surply , Dominique Haro , Fabrice Gantie , David Lambert
发明人： Frédéric Chelin , Thierry Surply , Dominique Haro , Fabrice Gantie , David Lambert
IPC分类号： F02K99/00 , E04B1/82
CPC分类号： B64D33/02 , B64D15/04 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/047 , F02K1/827 , Y10T137/0536
摘要： An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.
摘要翻译：连接到飞机机舱的进气口的声学处理面板包括至少一个声阻构造（30）和反射层（32），它们位于基本垂直于纵向方向的方向上（34）的肺泡细胞间隔开以允许用于霜冻治疗的热空气的通过，其特征在于，其包括用于热空气的管（36），每个管（36）分别由至少一个隔板从隔音层（30）延伸到反射层（32），以使得单元的带（34）在纵向方向上绝缘。

3. 发明申请

US20120060938A1 AIRCRAFT NACELLE COMPRISING A REINFORCED OUTER WALL 有权
标题翻译：包括增强外墙的飞机零件
公开(公告)号：US20120060938A1
公开(公告)日：2012-03-15
申请号：US13258588
申请日：2010-03-26
申请人： Frédéric Chelin , Thierry Surply
发明人： Frédéric Chelin , Thierry Surply
IPC分类号： F02K99/00
CPC分类号： B64D33/02 , B64C7/02 , F02C7/04 , F05D2240/14 , F05D2260/602 , Y02T50/671 , Y10T137/0536
摘要： An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).
摘要翻译：飞机机舱包括限定内部管道（42）的壁，所述内部管道（42）将空气流通向发电厂，在前部的唇缘（44）处并且在外部限定空腔（54）的外壁（46），其中所述外壁在其内表面包括布置在横向平面中的至少一个加强件（58），其特征在于，所述至少一个加强件（58）包括允许液体流动的至少一个排水开口通过所述加强件（58）沿着位于远离所述唇缘的排出口（56）的方向，以限制空气被吸入所述空腔（54）内的风险。

4. 发明授权

US09010084B2 Aircraft nacelle including an optimised acoustic processing system 有权
标题翻译：飞机机舱包括优化的声学处理系统
公开(公告)号：US09010084B2
公开(公告)日：2015-04-21
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： F02K3/02 , B64D15/04 , B64D33/02
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）。

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

US08434724B2 Air outlet system for aircraft leading edge 有权
标题翻译：飞机前端系统
公开(公告)号：US08434724B2
公开(公告)日：2013-05-07
申请号：US12745950
申请日：2008-12-01
申请人： Frédéric Chelin , Thierry Surply , Christophe Bourdeau
发明人： Frédéric Chelin , Thierry Surply , Christophe Bourdeau
IPC分类号： B64C21/04 , B64D15/02
CPC分类号： B64C21/04 , B64D29/02 , B64D33/02 , B64D2033/0226 , Y02T50/166
摘要： An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are arranged in an alternating fashion from one surface to the next, allowing air to pass on both sides of the aerodynamic surface.
摘要翻译：飞行器前缘由提供空气动力学流动的空气动力学表面延伸，并且其中设置空气排放物防止空气动力学流分离。空气排放物布置成至少两行，基本上平行于前缘并且以偏移方式布置成至少两个连续的行。在形成空气动力学表面的两个壁之间插入至少一个块。一方面，该块包括延伸空气动力学表面的外表面，接触形成空气动力学表面的第一壁的第一倾斜表面和接触形成空气动力学表面的第二壁的第二倾斜表面，另一方面手，突出和/或中空形状，其在倾斜表面处制成并且以从一个表面到下一个表面交替的方式布置，允许空气在空气动力学表面的两侧通过。

7. 发明授权

US09114884B2 Aircraft nacelle comprising a reinforced outer wall 有权
标题翻译：飞机机舱包括加强外壁
公开(公告)号：US09114884B2
公开(公告)日：2015-08-25
申请号：US13258588
申请日：2010-03-26
申请人： Frédéric Chelin , Thierry Surply
发明人： Frédéric Chelin , Thierry Surply
IPC分类号： F02C7/04 , B64D33/02 , B64C7/02
CPC分类号： B64D33/02 , B64C7/02 , F02C7/04 , F05D2240/14 , F05D2260/602 , Y02T50/671 , Y10T137/0536
摘要： An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).
摘要翻译：飞机机舱包括限定内部管道（42）的壁，所述内部管道（42）将空气流通向发电厂，在前部的唇缘（44）处并且在外部限定空腔（54）的外壁（46），其中所述外壁在其内表面包括布置在横向平面中的至少一个加强件（58），其特征在于，所述至少一个加强件（58）包括允许液体流动的至少一个排水开口通过所述加强件（58）沿着位于远离所述唇缘的排出口（56）的方向，以限制空气被吸入所述空腔（54）内的风险。

8. 发明申请

US20120177878A1 Part For And Method Of Repairing A Damaged Structure, In Particular An Airframe Skin, And A Repair Kit For Implementing It 有权
标题翻译：修复损坏结构，特别是机身皮肤的部件和方法，以及用于实施的修复工具
公开(公告)号：US20120177878A1
公开(公告)日：2012-07-12
申请号：US13344054
申请日：2012-01-05
申请人： Nicolas Boulet , Olivier Chaume , Frédéric Chelin
发明人： Nicolas Boulet , Olivier Chaume , Frédéric Chelin
IPC分类号： B32B3/24 , B32B1/00 , B23P6/00
CPC分类号： B64F5/0081 , B23P6/005 , B23P2700/01 , B29C73/14 , B29C2073/264 , B32B3/266 , B32B17/04 , B32B17/067 , B32B19/04 , B64F5/40 , Y10T29/49718 , Y10T29/49732 , Y10T29/49734 , Y10T29/49735 , Y10T29/53 , Y10T428/20 , Y10T428/24273 , Y10T428/24322 , Y10T428/24479 , Y10T428/24612 , Y10T428/249923
摘要： The invention aims to enable rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins, without necessitating any additional thickness compromising the transmission of waves. To this end it proposes a double internal/external plate constituted by a particular material. In one embodiment, the damaged structure having an external face and an internal face, the part features a substantially plane double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively, and a central hub connecting the internal plate and the external plate. A groove is thus formed between these plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.
摘要翻译：本发明旨在能够快速有效地修复损坏的金属结构，特别是机身机身外观，而不需要任何额外的厚度来损害波浪的传播。为此，它提出了由特定材料构成的双内/外板。在一个实施例中，损坏的结构具有外表面和内表面，该部分具有基本上平面的双内/外板，其适于紧固到金属结构的内表面和外表面，以及中心毂连接内部板和外部板。因此，在这些板之间形成凹槽。该部分由单个复合材料块构成，并且衬在该槽上的玻璃层可以位于板和结构之间。毂可以穿过其中至少一个适于允许连接通过结构的孔口。

9. 发明授权

US09353648B2 Panel for the acoustic treatment comprising hot air ducts and at least one annular channel 有权
公开(公告)号：US09353648B2
公开(公告)日：2016-05-31
申请号：US13573802
申请日：2012-10-03
申请人： Alain Porte , Frédéric Chelin , Grégory Albet
发明人： Alain Porte , Frédéric Chelin , Grégory Albet
IPC分类号： B64D15/04 , F01D25/24 , B64D33/02 , F02C7/045 , F02C7/24
CPC分类号： F01D25/24 , B64D15/04 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/24 , F05D2260/96 , Y02T50/672
摘要： An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel.

10. 发明授权

US08993090B2 Part for and method of repairing a damaged structure, in particular an airframe skin, and a repair kit for implementing it 有权
标题翻译：修理损坏的结构，特别是机身皮肤的部件和方法，以及用于实施的修理工具
公开(公告)号：US08993090B2
公开(公告)日：2015-03-31
申请号：US13344054
申请日：2012-01-05
申请人： Nicolas Boulet , Olivier Chaume , Frédéric Chelin
发明人： Nicolas Boulet , Olivier Chaume , Frédéric Chelin
IPC分类号： B32B3/24 , B32B43/00 , B29C73/14 , B23P6/00 , B64F5/00 , B32B17/04 , B32B19/04 , B29C73/26 , B32B17/06 , B32B3/26
CPC分类号： B64F5/0081 , B23P6/005 , B23P2700/01 , B29C73/14 , B29C2073/264 , B32B3/266 , B32B17/04 , B32B17/067 , B32B19/04 , B64F5/40 , Y10T29/49718 , Y10T29/49732 , Y10T29/49734 , Y10T29/49735 , Y10T29/53 , Y10T428/20 , Y10T428/24273 , Y10T428/24322 , Y10T428/24479 , Y10T428/24612 , Y10T428/249923
摘要： A repair part enables rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins having internal and external faces, without necessitating any additional thickness compromising the transmission of waves. To this end, the repair part includes a double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively. The repair part also includes a central hub connecting the internal plate and the external plate and forming a groove between the plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.
摘要翻译：修理部件能够快速有效地修复损坏的金属结构，特别是具有内部和外部表面的机身机身外壳，而不需要任何额外的厚度来损害波浪的传输。为此，修理部分包括分别固定在金属结构的内表面和外表面上的双内/外板。修理部分还包括连接内板和外板的中心毂，并在板之间形成凹槽。该部分由单个复合材料块构成，并且衬在该槽上的玻璃层可以位于板和结构之间。毂可以穿过其中至少一个适于允许连接通过结构的孔口。

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