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91. 发明公开

EP3986783A1 ADAPTIVE STRUCTURE 审中-公开
公开(公告)号：EP3986783A1
公开(公告)日：2022-04-27
申请号：EP20734600.8
申请日：2020-06-18
申请人： GKN Aerospace Services Limited
发明人： VAN DER EIJK, Wouter
IPC分类号： B64C3/00 , B64C3/48 , B64C3/44 , B64C3/26

92. 发明授权

EP2635427B1 LAMINATE STRUCTURE 有权
标题翻译：层压结构
公开(公告)号：EP2635427B1
公开(公告)日：2017-11-29
申请号：EP11778944.6
申请日：2011-10-27
申请人： GKN Aerospace Services Limited
发明人： GAWN, Marcus , ANDERSON, Paul , MARENGO, Giovanni
IPC分类号： B29C70/30 , B29C70/08
CPC分类号： B29C70/021 , B29C70/083 , B29C70/30 , F01D25/24 , Y10T156/10 , Y10T428/24752

93. 发明授权

EP2961655B1 ICE PROTECTION SYSTEM 有权
标题翻译： ICE保护系统
公开(公告)号：EP2961655B1
公开(公告)日：2017-08-16
申请号：EP14709385.0
申请日：2014-02-28
申请人： GKN Aerospace Services Limited
发明人： ENGLISH, Peter , RICHARDS, Thomas Stephen Rowe , ARMSTRONG, David John
IPC分类号： B64D15/20
CPC分类号： B64D15/22 , B64D15/20

94. 发明授权

EP2627498B1 METHOD OF MANUFACTURING A COMPOSITE STRUCTURE AND COMPOSITE STRUCTURE OBTAINED THEREBY 有权
标题翻译：用于生产复合结构，从而方法获得的复合材料结构
公开(公告)号：EP2627498B1
公开(公告)日：2015-12-30
申请号：EP11774091.0
申请日：2011-10-11
申请人： GKN Aerospace Services Limited
发明人： RALFS, Benjamin , MORAM, John
IPC分类号： B29C70/38 , B29C33/26 , B29C70/54
CPC分类号： B32B37/18 , B29C33/0011 , B29C33/20 , B29C33/485 , B29C70/382 , B29C70/386 , B29C70/54 , B29L2031/7504 , B32B38/0004 , Y10T156/108

95. 发明授权

EP2370315B1 FLÄCHIGES BAUTEIL EINES FLUGGERÄTES UND VERFAHREN ZU DESSEN HERSTELLUNG 有权
标题翻译：扁平组件上飞行设备和方法及其
公开(公告)号：EP2370315B1
公开(公告)日：2013-01-09
申请号：EP09763921.5
申请日：2009-11-24
申请人： GKN Aerospace Services Limited
发明人： RICHMOND, Nolan , RITSCHEL, Thomas
IPC分类号： B64C1/06 , B64C1/12 , B64C3/18
CPC分类号： B64C1/12 , B64C1/064 , B64C3/187 , Y02T50/43 , Y10T156/1007 , Y10T428/24612 , Y10T428/24752 , Y10T428/24802
摘要： The invention relates to a planar component (1) of an aircraft (2) which component defines an area (3) having a material thickness (4). In order to increase the dent resistance in at least part of the area or subareas (7) that are defined by webs (5) having a web height (6), at least one reinforcing bead (8) having a bead length (9) extends between the webs (5) across the subarea (7). The invention also relates to a method of production which particularly allows the production of such a planar component in an autoclave.

96. 发明公开

EP2528813A1 ELECTROTHERMAL HEATER MAT 有权
标题翻译：电热加热垫
公开(公告)号：EP2528813A1
公开(公告)日：2012-12-05
申请号：EP11702860.5
申请日：2011-01-31
申请人： GKN Aerospace Services Limited
发明人： LEWIS, Stuart, Martin , WINTER, Nicholas, John , ENGLISH, Peter
IPC分类号： B64D15/12 , H05B3/36
CPC分类号： B64D15/12 , B64D2033/0233 , H05B3/36 , H05B2203/013 , H05B2203/017 , H05B2203/033 , H05B2214/02
摘要： An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a temperature sensor (507). Each dielectric layer (50-58) comprises thermoplastic material, and the temperature sensor (507) comprises a sprayed metal track (5010, 5012) deposited on a substrate (50, 5019) comprising thermoplastic material. The substrate may be one of the dielectric layers (50) or a separate carrier (5019) which is smaller than the dielectric layers (50-58). The substrate (50, 5019) is laminated to at least a first one of the dielectric layers (53, 58) and the thermoplastic material of the substrate is (i) the same as the thermoplastic material of the first dielectric layer such that the thermoplastic material of the substrate is dispersed or merged into the thermoplastic material of the first dielectric layer or (ii) compatible with the thermoplastic material of the first dielectric layer such that the thermoplastic material of the substrate is fused to the thermoplastic material of the first dielectric layer. Thus, the formation of an undesirable discontinuity at the interface between the substrate (50, 5019) and the first dielectric layer (53, 58) is substantially prevented or minimised.
摘要翻译：电热加热垫（3）被设置用于飞机（1）等的防冰系统。加热垫（3）是层压加热垫，并且包括介电层（50-58），加热元件（501）和温度传感器（507）。每个介电层（50-58）包括热塑性材料，并且温度传感器（507）包括沉积在包括热塑性材料的基底（50,5019）上的喷射金属轨道（5010,5012）。衬底可以是介电层（50）之一或者小于介电层（50-58）的单独的载体（5019）。衬底（50,5019）被层压到介电层（53,58）中的至少第一个，并且衬底的热塑性材料（i）与第一介电层的热塑性材料相同，使得热塑性材料基板的材料分散或合并到第一电介质层的热塑性材料中或（ii）与第一电介质层的热塑性材料相容，使得基板的热塑性材料熔合到第一电介质层的热塑性材料。因此，在衬底（50,5019）与第一介电层（53,58）之间的界面处形成不希望的不连续性基本上被阻止或最小化。

97. 发明公开

EP2370315A2 FLÄCHIGES BAUTEIL EINES FLUGGERÄTES UND VERFAHREN ZU DESSEN HERSTELLUNG 有权
标题翻译：扁平组件上飞行设备和方法及其
公开(公告)号：EP2370315A2
公开(公告)日：2011-10-05
申请号：EP09763921.5
申请日：2009-11-24
申请人： GKN Aerospace Services Limited
发明人： RICHMOND, Nolan , RITSCHEL, Thomas
IPC分类号： B64C1/06 , B64C1/12 , B64C3/18
CPC分类号： B64C1/12 , B64C1/064 , B64C3/187 , Y02T50/43 , Y10T156/1007 , Y10T428/24612 , Y10T428/24752 , Y10T428/24802
摘要： The invention relates to a planar component (1) of an aircraft (2) which component defines an area (3) having a material thickness (4). In order to increase the dent resistance in at least part of the area or subareas (7) that are defined by webs (5) having a web height (6), at least one reinforcing bead (8) having a bead length (9) extends between the webs (5) across the subarea (7). The invention also relates to a method of production which particularly allows the production of such a planar component in an autoclave.

98. 发明授权

EP2129579B1 AIR INTAKE DUCT WITH THERMAL ANTI-ICING SYSTEM 有权
标题翻译： WITH A除冰进风通道
公开(公告)号：EP2129579B1
公开(公告)日：2011-02-23
申请号：EP08718624.3
申请日：2008-03-05
申请人： GKN Aerospace Services Limited
发明人： GREGORY, Karl , SHEPPARD, Michael, James , ATTRILL, Scott
IPC分类号： B64D15/04
CPC分类号： B64D15/04 , B64D2033/0233
摘要： An air intake duct of an aircraft engine or other component is provided with a thermal anti-icing system. The front of the air intake duct comprises a toroidal outer skin (16) which forms, with a toroidal, internal bulkhead (18), a toroidal plenum (8) about the centre line (26). The bulkhead has an inner edge nearest the centre line. Within the plenum there is a toroidal inner skin (9) defining with the outer skin a substantially continuous toroidal channel (19). Hot air is supplied via an inlet (7) to the plenum (8). The air flows into an inlet (14) at an end of channel (19) and out of an outlet (11) through the bulkhead (18). This provide more heat to the leading edge of the duct, and to the surface of the duct facing the centre line, than to other parts of the duct to prevent build up of ice which may enter, and damage, the engine. This reduces the mass flow of hot air needed for de-icing.

99. 发明公开

EP2252442A1 SEMI-RIGID TOOL 审中-公开
标题翻译：半刚性工具
公开(公告)号：EP2252442A1
公开(公告)日：2010-11-24
申请号：EP09702373.3
申请日：2009-01-16
申请人： GKN Aerospace Services Limited
发明人： BARBER, Scott , GRAINGER, Philip
IPC分类号： B29C33/38 , B29C43/36 , B29C70/44
CPC分类号： B29C70/44 , B29C33/00 , B29C43/12 , B29C43/3642 , Y10T29/49 , Y10T29/49036
摘要： The present invention relates to a manufacturing tool (13, 14) and method for use in forming polymer matrix composite products such as carbon fibre composite products. The tool comprising a first and a second portion defining a cavity (15) therebetween in which the product is built before curing. The rigidity of the second portion (13) of the tool is selected based on the required deflection of the second portion of the tool under the curing conditions, in order to maintain pressure on the laminate during the entire cure. The second upper portion (13) is shown haring varying thicknesses (16A, 16B and 16C) which results in different rigidity of these regions.

100. 发明公开

EP2129579A1 THERMAL ANTI-ICING SYSTEM 有权
标题翻译： WITH A除冰进风通道
公开(公告)号：EP2129579A1
公开(公告)日：2009-12-09
申请号：EP08718624.3
申请日：2008-03-05
申请人： GKN Aerospace Services Limited
发明人： GREGORY, Karl , SHEPPARD, Michael, James , ATTRILL, Scott
IPC分类号： B64D15/04
CPC分类号： B64D15/04 , B64D2033/0233
摘要： An air intake duct of an aircraft engine or other component is provided with a thermal anti-icing system. The front of the air intake duct comprises a toroidal outer skin (16) which forms, with a toroidal, internal bulkhead (18), a toroidal plenum (8) about the centre line (26). The bulkhead has an inner edge nearest the centre line. Within the plenum there is a toroidal inner skin (9) defining with the outer skin a substantially continuous toroidal channel (19). Hot air is supplied via an inlet (7) to the plenum (8). The air flows into an inlet (14) at an end of channel (19) and out of an outlet (11) through the bulkhead (18). This provide more heat to the leading edge of the duct, and to the surface of the duct facing the centre line, than to other parts of the duct to prevent build up of ice which may enter, and damage, the engine. This reduces the mass flow of hot air needed for de-icing.

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