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121. 发明申请

WO2015068082A1 HEALTH MONITORING OF COMPOSITE STRUCTURES 审中-公开
标题翻译：复合结构的健康监测
公开(公告)号：WO2015068082A1
公开(公告)日：2015-05-14
申请号：PCT/IB2014/065689
申请日：2014-10-29
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： MOFAKHAMI, Mohammad Reza , PINSONNAULT, Jerome , OLSEN, Alain
IPC分类号： G01N29/04 , B64F5/00 , G01H1/00 , G01M7/00
CPC分类号： G01N29/043 , B64D45/00 , B64D2045/0085 , B64F5/60 , G01M5/0033 , G01M5/0066 , G01N29/04 , G01N2291/0231 , G01N2291/0289 , G01N2291/048 , G01N2291/2694 , G07C5/008
摘要： The present disclosure describes devices, assemblies, apparatus and methods useful in conducting health monitoring of structures including monitoring for structural damage and liquid (e.g., water, fuel, anti-Icing fluid, moisture, etc.) Ingress in composite sandwich-type structures of mobile platforms. An exemplary method for detecting water Ingress in a structure comprises: introducing mechanical energy into the structure; sensing the mechanical energy transmitted through the structure; and determining the existence of water ingress in the structure based on the sensed mechanical energy.
摘要翻译：本公开描述了用于进行结构健康监测的装置，组件，装置和方法，包括对结构损伤和液体（例如，水，燃料，抗结冰流体，水分等）的监测。复合夹层结构中的入口移动平台。用于检测结构中的水入口的示例性方法包括：将机械能引入到结构中; 感测通过结构传递的机械能; 并基于感测到的机械能来确定结构中的水入口的存在。

122. 发明申请

WO2015063750A1 GUIDING APPARATUS 审中-公开
标题翻译：指导装置
公开(公告)号：WO2015063750A1
公开(公告)日：2015-05-07
申请号：PCT/IB2014/065800
申请日：2014-11-04
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： BOURCIER, Greg
IPC分类号： B23Q9/00 , B23Q9/02 , B23Q35/10 , B64F5/00
CPC分类号： B23Q35/103 , B23Q9/0057 , B23Q9/02 , B64F5/10 , B64F5/40
摘要： A guiding apparatus for replicating the outline of a second component to a first component, the guiding device comprising a gripping unit adapted to grippingly engage the first component. A guide unit is adapted to contact an edge of the second component, the edge defining the outline to replicate. A supporting unit is adapted to receive a machining tool, the supporting unit orienting the machining tool, when such machining tool is installed, relative to the guide unit for concurrent movement of the guide unit and the machining tool along an axial direction of the first and second components while moving along the first component. A method for replicating an outline of a second component to a first component is also provided, for components such as aircraft fuselage sections.
摘要翻译：一种用于将第二部件的轮廓复制到第一部件的引导装置，所述引导装置包括适于夹紧地接合所述第一部件的夹持单元。引导单元适于接触第二部件的边缘，边缘限定轮廓以进行复制。支撑单元适于接纳加工工具，当安装这种加工工具时，支撑单元相对于引导单元定向加工工具，用于引导单元和加工工具沿着第一和/ 第二部件沿着第一部件移动。还提供了用于将第二部件的轮廓复制到第一部件的方法，用于诸如飞机机身部分的部件。

123. 发明申请

WO2015036940A1 METHOD OF FORMING A COMPOSITE MEMBER AND ASSEMBLY THEREFOR 审中-公开
标题翻译：形成复合构件的方法及其组装
公开(公告)号：WO2015036940A1
公开(公告)日：2015-03-19
申请号：PCT/IB2014/064400
申请日：2014-09-10
申请人： SHORT BROTHERS PLC , BOMBARDIER INC.
发明人： FERNANDES, Louis , LEMIEUX, Marc , EURY, Youenn , ATARSIA, Abdelatif
IPC分类号： B29C70/34 , B29C70/44 , B29C33/48 , B29C33/76 , B29L24/00
CPC分类号： B29C70/342 , B29C33/485 , B29C33/76 , B29C65/481 , B29C66/5326 , B29C66/63 , B29C70/34 , B29C70/446 , B29L2009/00 , B29L2022/00 , B29L2024/00 , B29L2031/3082
摘要： A method of preparing a composite element for forming a composite assembly having a cavity is disclosed. The method includes laying a barrier layer on a surface of the composite element which defines at least part of the cavity. A support assembly including a mandrel (38) and a film bag (40) extending on the surface of the mandrel is positioned with the film bag against the barrier layer. A sealed enclosure containing the composite element is formed through sealing engagement with the film bag. The pressure within the sealed enclosure is reduced, and the mandrel is separated from the film bag while maintaining the film bag positioned against the barrier layer. In one embodiment, the element is a stringer and is positioned against a skin. An assembly for forming a composite member is also provided.
摘要翻译：公开了一种制备用于形成具有空腔的复合组件的复合元件的方法。该方法包括在限定至少部分空腔的复合元件的表面上铺设阻挡层。包括在心轴表面上延伸的心轴（38）和薄膜袋（40）的支撑组件被定位成使薄膜袋抵靠阻挡层。通过与薄膜袋的密封接合形成包含复合元件的密封外壳。密封外壳内的压力降低，心轴与薄膜袋分离，同时保持薄膜袋位于阻挡层上。在一个实施例中，元件是纵梁并且抵靠皮肤定位。还提供了一种用于形成复合构件的组件。

124. 发明申请

WO2015025262A1 ABNORMAL AIRCRAFT RESPONSE MONITOR 审中-公开
标题翻译：异常飞机反应监控
公开(公告)号：WO2015025262A1
公开(公告)日：2015-02-26
申请号：PCT/IB2014/063956
申请日：2014-08-18
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： BURTE, Gregory
IPC分类号： B64C13/42 , G05D1/00
CPC分类号： G05D1/0077 , B64C13/503
摘要： An aircraft flight control system includes at least two flight control computers at least one of which is utilized at any one time to control aircraft flight, each of the at least two flight control computers having at least two processors, each processor being responsive to an aircraft input signal indicative of at least one of a plurality of aircraft flight parameters and being responsive to control laws to provide a control output command signal indicative of a desired control of an aircraft flight control surface. Also, at least one of the at least two processors for each of the at least two flight control computers comprises an abnormal response monitor that is responsive to at least one aircraft input signal indicative of at least one of a plurality of aircraft flight parameters to determine whether the control output command signal is within an acceptable value.
摘要翻译：飞行器飞行控制系统包括至少两个飞行控制计算机，其中至少一个飞行控制计算机在任何一个时间用于控制飞行器飞行，所述至少两个飞行控制计算机中的每一个具有至少两个处理器，每个处理器响应飞行器输入信号，其指示多个飞行器飞行参数中的至少一个，并响应于控制规律提供指示飞机飞行控制表面的期望控制的控制输出命令信号。此外，用于至少两个飞行控制计算机中的每一个的至少两个处理器中的至少一个包括响应于至少一个飞行器输入信号的异常响应监视器，其指示多个飞行器飞行参数中的至少一个以确定控制输出命令信号是否在可接受的值内。

125. 发明申请

WO2014199212A1 AIRCRAFT SIDESTICK PRIORITY AND DUAL INPUT CONTROL LOGIC 审中-公开
标题翻译：飞机航空器优先级和双输入控制逻辑
公开(公告)号：WO2014199212A1
公开(公告)日：2014-12-18
申请号：PCT/IB2014/000997
申请日：2014-06-09
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： OUELLETTE, Benoit , DUCHESNE, Sophie , LECOQ, Frederic
IPC分类号： G05D1/00 , B64C13/12
CPC分类号： G05D1/0061 , B64C13/12 , G05D1/0077
摘要： The present invention relates to a fly-by-wire type of aircraft flight control system having a pair of sidesticks for pilot and co-pilot input, respectively, and having logic that controls the priority of input as between the two sidesticks in certain aircraft flight situations. It allows either the pilot or co-pilot to ensure that his/her sidestick is the only one issuing flight control commands at any one moment in time by first pressing a simple latch button located, for example, on the glareshield in the cockpit and then maneuvering the sidestick in the desired manner to effectuate flight control, e.g., pitch and/or roll, of the aircraft.
摘要翻译：技术领域本发明涉及一种飞控飞行控制系统，其具有用于飞行员和副飞行员输入的一对侧线，并且具有控制在某些飞行器飞行中的两个侧线之间的输入优先级的逻辑的情况。它允许飞行员或副驾驶员确保他/她的侧线是唯一一个在任何时刻发出飞行控制命令的人，首先按下一个简单的闩锁按钮，例如位于驾驶舱内的glareshield上以期望的方式操纵侧线以实现飞行器的飞行控制，例如俯仰和/或滚动。

126. 发明申请

WO2014135943A3 AIRCRAFT FLOOR INCORPORATING A GROUND PLANE 审中-公开
标题翻译：装有地面平面的飞机地板
公开(公告)号：WO2014135943A3
公开(公告)日：2014-12-04
申请号：PCT/IB2014000209
申请日：2014-02-26
申请人： BOMBARDIER INC , SHORT BROTHERS PLC
发明人： ROBOREL DE CLIMENS LODY , DESY PHILIPPE , GAUDREAU JEAN-GUY
IPC分类号： B64C1/18 , B64D45/02 , H02G3/04
CPC分类号： B64C1/18 , B64D45/02 , F16M13/02
摘要： A system for shielding of at least one component (28) within an aircraft (10) includes a floor panel disposed at least partially between joists (38) supporting a floor (30) within the aircraft and a ground plane (44) connected to a bottom surface of the floor panel. The ground plane extends at least partially between adjacent joists. At least one bracket (52) electrically connects the ground plane to at least one of the joists.
摘要翻译：用于遮蔽飞行器（10）内的至少一个部件（28）的系统包括至少部分地布置在支撑飞机内的地板（30）的托梁（38）之间的底板和连接到飞机底板底面。接地平面至少部分延伸在相邻的托梁之间。至少一个托架（52）将接地平面电连接到至少一个托梁。

127. 发明申请

WO2014136085A1 TANK WALL CONNECTOR SYSTEM 审中-公开
标题翻译：油罐连接器系统
公开(公告)号：WO2014136085A1
公开(公告)日：2014-09-12
申请号：PCT/IB2014/059501
申请日：2014-03-06
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： SOURBES, Guillaume , DÉSY, Philippe , GAUDREAU, Jean-Guy
IPC分类号： B64D37/00 , B64D37/32
CPC分类号： B64D37/32 , B64D37/005 , B64D37/02
摘要： A tank wall connector system (10) for use with a composite tank, the connector comprises a connector (20, 22) having a body extending from an interior of the tank to an exterior of the tank when installed through a hole in the composite tank. The connector has a first electrical conductivity property. An interface (13) is positioned between the connector (20, 22) and a wall (A) of the composite tank when installed to the tank thereby preventing physical contact between the connector (20, 22) and the tank wall (A) in the interior of the tank, the interface (13) having a second electrical conductivity property, different from the first electrical conductivity property.
摘要翻译：一种与复合罐一起使用的罐壁连接器系统（10），所述连接器包括连接器（20,22），所述连接器具有从所述罐的内部延伸到所述罐的外部的主体，当通过所述复合罐中的孔安装时。连接器具有第一导电性。当安装到箱体上时，接口（13）位于复合罐的连接器（20,22）和壁（A）之间，从而防止连接器（20,22）和罐壁（A）之间的物理接触罐的内部，界面（13）具有不同于第一导电性能的第二导电性质。

128. 发明申请

WO2014135948A2 AFT PYLON FAIRING FOR AIRCRAFT 审中-公开
公开(公告)号：WO2014135948A2
公开(公告)日：2014-09-12
申请号：PCT/IB2014/000223
申请日：2014-02-28
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： SHEPHARD, Kevin , YOUNG, Jeffrey, E. , BEEDY, Lyle
IPC分类号： B64D29/02
CPC分类号： B64D29/06 , B64C7/02 , B64D29/02 , B64D33/04 , B64D45/00
摘要： Aft fairings (22) for aircraft pylons (14) are disclosed. In one example, a fairing (22) comprises: two opposite side panels (24) extending generally along a longitudinal direction of the fairing (22); a plurality of transverse ribs (28) interconnecting the two opposite side panels (24); and a heat shield (30) for exposure to a primary flow (16) of an aircraft engine (10). The heat shield (30) comprises transversely opposed side end portions (30A, 30C) and a mid portion (30B) disposed between the transversely opposed side end portions (30A, 30C). The heat shield (30) is secured to the ribs (28) via the mid portion (30B) of the heat shield (30). The transversely opposed side end portions (30A, 30C) are permitted to move outwardly from the mid portion (30B) due to thermal expansion of the heat shield (30).
摘要翻译：公开了用于飞机挂架（14）的后整流罩（22）。在一个示例中，整流装置（22）包括：大致沿着整流装置（22）的纵向方向延伸的两个相对的侧面面板（24）; 连接两个相对的侧板（24）的多个横向肋（28）; 和用于暴露于飞机发动机（10）的主流（16）的隔热罩（30）。隔热罩30包括横向相对的侧端部分30A和30C以及设置在横向相对的侧端部分30A和30C之间的中间部分30B。隔热罩（30）经由隔热罩（30）的中间部分（30B）固定到肋（28）。由于隔热罩（30）的热膨胀，允许横向相对的侧端部分（30A，30C）从中间部分（30B）向外移动。

129. 发明申请

WO2014135946A1 ELECTRIC BRAKING SYSTEM WITH POWER CONSERVATION AND METHOD OF OPERATING THE SAME 审中-公开
标题翻译：具有功率保护的电动制动系统及其操作方法
公开(公告)号：WO2014135946A1
公开(公告)日：2014-09-12
申请号：PCT/IB2014/000214
申请日：2014-02-27
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： DI ZAZZO, Marco , PLANTE, Bertrand
IPC分类号： B60T8/17 , B64C25/44
CPC分类号： B64C25/44 , B60T8/1703 , B60T8/885 , B60T2270/414 , B64C25/34 , B64D2221/00
摘要： A method of operating electric brakes (30, 32, 34) on an aircraft (10) in a low power mode of operation includes determining if the aircraft is in a first configuration, if the aircraft is in the first configuration, disengaging power to the electric brakes (30, 32, 34) the from all power supplies (40, 42), determining if the aircraft (10) is in a second configuration, if the aircraft is in the second configuration, engaging power to the electric brakes (30, 32, 34) from one of the power supplies (40, 42), determining if the aircraft (10) is in a third configuration, and if the aircraft (10) is in the third configuration, engaging power to the electric brakes (30, 32, 34) from at least two of the power supplies (40, 42).
摘要翻译：在低功率操作模式下在飞机（10）上操作电制动器（30,32,34）的方法包括确定飞行器是否处于第一配置，如果飞行器处于第一配置，则将功率分离到电动制动器（30,32,34）从所有电源（40,42）中确定飞行器（10）是否处于第二配置，如果飞行器处于第二配置，则将电力接合到电制动器（30,42），32,34），确定所述飞行器（10）是否处于第三构造，并且如果所述飞行器（10）处于所述第三构造，则将电力接合到所述电制动器（ 30,32,34）从至少两个电源（40,42）中取出。

130. 发明申请

WO2014135939A2 INTERFACE BETWEEN FIRE SUPPRESSANT CONDUIT AND CARGO COMPARTMENT OF AN AIRCRAFT 审中-公开
标题翻译：消防队员与飞机货舱之间的接口
公开(公告)号：WO2014135939A2
公开(公告)日：2014-09-12
申请号：PCT/IB2014000197
申请日：2014-02-24
申请人： BOMBARDIER INC , SHORT BROTHERS PLC
发明人： EL HADDAD ANTHONY , DESY PHILIPPE , GAUDREAU JEAN-GUY
IPC分类号： A62C3/08
CPC分类号： A62C3/08 , A62C35/68 , B64D45/00 , B64D2045/009
摘要： Apparatus and methods related to fire suppression in cargo compartments of aircraft are disclosed. An exemplary apparatus provides an interface (38) between a fire suppressant conduit (18) and a cargo panel (28) of a cargo compartment (12) of an aircraft (10). The apparatus comprises an adaptor (40) configured to provide the fire suppressant conduit (18) access to the cargo compartment (12) through the cargo panel (28) and a sealing member (42) configured to provide a seal between the adaptor (40) and the fire suppressant conduit (18). The adaptor (40) comprises an aperture (56) for receiving the fire suppressant conduit (18) where the aperture (56) is sized to permit passage of a nozzle (36) of the fire suppressant conduit (18) therethrough. Associated methods (600, 700) for removing the cargo panel (28) of the cargo compartment (12) of the aircraft (10) without disassembly of the nozzle (36) of the fire suppressant conduit (18) are also disclosed.
摘要翻译：披露了与飞机货舱内的灭火有关的装置和方法。示例性装置提供了消防管道（18）和飞机（10）的货舱（12）的货物面板（28）之间的接口（38）。该装置包括适配器（40），其配置成提供消防管道（18）通过货物面板（28）进入货物舱（12）;以及密封构件（42），该密封构件构造成在适配器（40））和消防管道（18）。适配器（40）包括用于接收消防管道（18）的孔口（56），其中孔口（56）的尺寸设置成允许消防管道（18）的喷嘴（36）通过其中。还公开了用于移除飞行器（10）的货舱（12）的货物面板（28）而不拆卸消防管道（18）的喷嘴（36）的相关方法（600,700）。

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