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21. 发明申请

WO2017029569A1 ATTACHMENT BRACKET AND SUPPORT ASSEMBLY 审中-公开
标题翻译：附件支架和支撑总成
公开(公告)号：WO2017029569A1
公开(公告)日：2017-02-23
申请号：PCT/IB2016/054622
申请日：2016-08-01
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： GALLIEN, René , DESHAIES, Martin
IPC分类号： F16B11/00 , H02G3/00
CPC分类号： H02G3/32 , F16B5/0685 , F16B7/0433 , F16B11/006 , F16B37/044 , F16B37/048
摘要： A support assembly (10) having a structural element (12) having first and second non-parallel adjoining surfaces (18), a bracket (14) attached to the structural element (12), and a component support (16). The bracket (14) has a first flange (20) including a first attachment surface (24) adhesively bonded to the first surface (18) of the structural element (12), a second flange (20) including a second attachment surface (24) adhesively bonded to the second surface (18) of the structural element (12), and a connection portion (48) interconnecting the first and second flanges (20), the connection portion (48) extending spaced from the structural element (12) such that a gap (52) is defined therebetween. The component support (16) is engaged to the first flange (20). The connection portion (48) may have a lower resistance to rupture than that of the first and second flanges (20). A method of removably securing a component to a structural element is also discussed.
摘要翻译：具有具有第一和第二非平行相邻表面（18）的结构元件（12）的支撑组件（10），附接到结构元件（12）的支架（14）和部件支撑件（16）。支架（14）具有第一凸缘（20），第一凸缘（20）包括粘合地结合到结构元件（12）的第一表面（18）的第一附接表面（24）;第二凸缘（20），包括第二附接表面）连接到所述结构元件（12）的第二表面（18），以及连接所述第一和第二凸缘（20）的连接部分（48），所述连接部分（48）与所述结构元件（12）间隔开延伸，使得它们之间限定间隙（52）。部件支撑件（16）接合到第一法兰（20）。连接部分（48）可以具有比第一和第二凸缘（20）的抗破坏性更低的抗破坏性。还讨论了将组件可移除地固定到结构元件的方法。

22. 发明申请

WO2017001984A1 AIRCRAFT WITH DISTRIBUTED HYDRAULIC SYSTEM 审中-公开
标题翻译：具有分布式液压系统的飞机
公开(公告)号：WO2017001984A1
公开(公告)日：2017-01-05
申请号：PCT/IB2016/053757
申请日：2016-06-23
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： NFONGUEM, Gustave , ILIESCU, Vlad , ARDMAN, Avraham
IPC分类号： B64C13/50 , B64C13/42
CPC分类号： B64C13/42 , B64C5/10 , B64C9/00 , B64C13/503 , B64C13/504 , B64C2009/005 , Y02T50/44
摘要： An aircraft comprises an aircraft structure, a flight control surface attached to the aircraft structure, and a local hydraulic power pack disposed proximal to the flight control surface. The local hydraulic power pack is configured to provide pressurized hydraulic fluid for actuating the flight control surface. The local hydraulic power pack comprises a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.
摘要翻译：飞机包括飞机结构，附接到飞行器结构的飞行控制表面以及靠近飞行控制表面设置的局部液压动力组件。局部液压动力组件构造成提供用于致动飞行控制表面的加压液压流体。本地液压动力组件包括用于液压流体的储存器和用于对液压流体加压的两个液压泵。

23. 发明申请

WO2016189420A1 AIRCRAFT AIR QUALITY MONITORING SYSTEM AND METHOD 审中-公开
标题翻译：飞机空气质量监测系统和方法
公开(公告)号：WO2016189420A1
公开(公告)日：2016-12-01
申请号：PCT/IB2016/052831
申请日：2016-05-16
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： FAGUNDES, Sandro, A.S. , MEISLITZER, Boris , AYRE, Keith
IPC分类号： B64D13/00 , B64D13/06
CPC分类号： B64D13/06 , B64D13/00 , B64D45/00 , B64D2013/0688 , Y02T50/54 , Y02T50/56
摘要： Air quality sensors are incorporated into an aircraft ventilation system in order to detect the nature and concentration of possible contaminants in the air flow passages. Data from the sensors may also be used to monitor air quality trends, determine corrective measures, and provide maintenance alerts. The sensors are provided at strategic locations throughout the ventilation system, such as before and/or after an air compressor and before and/or after a recirculation system, in order to identify where the problem is occurring.
摘要翻译：空气质量传感器被并入到飞机通风系统中，以便检测空气流通道中可能的污染物的性质和浓度。传感器的数据也可用于监测空气质量趋势，确定纠正措施，并提供维护警报。这些传感器设置在整个通风系统的战略位置，例如在空气压缩机之前和/或之后，以及再循环系统之前和/或之后，以便确定出现问题的位置。

24. 发明申请

WO2016157099A1 COMBINED AIRCRAFT MAINTENANCE ROUTING AND MAINTENANCE TASK SCHEDULING 审中-公开
标题翻译：组合航空维修路线和维护任务调度
公开(公告)号：WO2016157099A1
公开(公告)日：2016-10-06
申请号：PCT/IB2016/051807
申请日：2016-03-30
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： SAFAEI, Nima
IPC分类号： G06Q10/06 , G06Q10/00
CPC分类号： G06Q10/20 , G06Q10/06 , G06Q10/0631 , G06Q10/1097 , G06Q50/28
摘要： A method and system for coordinating aircraft maintenance routing and scheduling for a fleet of aircraft over a given time period is described. The method comprises receiving an initial list of due maintenance tasks based on aircraft information of the fleet and a proposed fleet utilization distribution; generating a set of aircraft routes for the fleet, the routes comprising maintenance opportunities for the due maintenance tasks, the due maintenance tasks being considered as aggregated maintenance constraints for generation of the aircraft routes; scheduling the due maintenance tasks into the maintenance opportunities while respecting target due dates; and in case of infeasibility for maintenance task scheduling within the maintenance opportunities of the aircraft routes, regenerating the set of aircraft routes for the fleet using the aggregated maintenance constraints and additional constraints, and rescheduling the due maintenance tasks using the regenerated set of aircraft routes.
摘要翻译：描述了用于在给定时间段内协调飞机维修路线和调度的方法和系统。该方法包括基于机队的飞机信息和提出的舰队利用分布来接收适当维护任务的初始列表; 为船队生成一套飞机航线，路线包括适当维护任务的维护机会，适当的维护任务被认为是生成飞机航路的总体维护限制; 将适当的维护任务安排到维护机会，同时遵守目标到期日; 并且在飞机路线的维护机会内的维护任务调度不可行的情况下，使用汇总的维护约束和附加约束再生该组航空器航线，并且使用再生的一组航空器路线重新安排适当的维护任务。

25. 发明申请

WO2016151423A1 SIMULATION OF LOADS ON AEROSTRUCTURES DURING AIRCRAFT ASSEMBLY 审中-公开
标题翻译：航空器组装期间航空器载荷的模拟
公开(公告)号：WO2016151423A1
公开(公告)日：2016-09-29
申请号：PCT/IB2016/051287
申请日：2016-03-07
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： LECLERC, Jean-Marc
IPC分类号： B64F5/00
CPC分类号： B64F5/60 , B64D13/02 , B64D43/02 , B64F5/10 , G01C21/165
摘要： Methods and systems useful during assembly of aircraft are disclosed. One such method comprises loading a fuselage of the aircraft that is unassembled with a wing of the aircraft to obtain a configuration of the fuselage corresponding to when the fuselage is assembled with the wing. The method also comprises calibrating a device of a navigation system of the aircraft when the fuselage is unassembled with the wing and is being loaded to obtain the loaded configuration and, after calibrating the device of the navigation system, assembling the fuselage with the wing.
摘要翻译：公开了在组装飞机期间有用的方法和系统。一种这样的方法包括加载与飞机的翼部未组装的飞行器的机身，以获得与机身与机翼组装时对应的机身的配置。该方法还包括当机身与翼组装在一起时，校准飞行器的导航系统的装置，并且被加载以获得加载的配置，并且在校准导航系统的装置之后，将机身与机翼组装。

26. 发明申请

WO2016147077A1 SYNCHRONIZATION OF AIRCRAFT ENGINES 审中-公开
标题翻译：飞机发动机同步
公开(公告)号：WO2016147077A1
公开(公告)日：2016-09-22
申请号：PCT/IB2016/051278
申请日：2016-03-07
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： COLAVINCENZO, Stephen , BRODEUR, Andre , CARON L’ECUYER, Alexis , BOGDAN, Mirel , JOVICIC, Dragan
IPC分类号： B64D31/12 , F02C9/18 , F02C9/28 , F02C9/42
CPC分类号： B64D31/12 , F02C9/18 , F02C9/28 , F02C9/42 , F05D2220/323
摘要： Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine.
摘要翻译：公开了一种用于改善飞机上两个或多个发动机同步的方法和相关装置。可以使用这种方法，其中每个发动机包括第一阀芯和第二阀芯，并且其中第一发动机的第一阀芯的转速已基本上与第二发动机的第一阀芯的转速同步。一种示例性方法包括接收用于控制第一发动机的感测参数的值; 增加价值的偏见; 并且使用所述偏压值来控制所述第一发动机相对于所述第一发动机的所述第一阀芯的转速使所述第一发动机的所述第二阀芯的转速发生变化。

27. 发明申请

WO2016142907A1 ASSEMBLY OF COMPONENTS WITH DATUM FEATURES 审中-公开
标题翻译：具有数据特征的组件组装
公开(公告)号：WO2016142907A1
公开(公告)日：2016-09-15
申请号：PCT/IB2016/051380
申请日：2016-03-10
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： REGNAULT, Laurent , ILIOPOULOS, Alexandros , SIROIS, Sébastien
IPC分类号： B64F5/00 , G05B19/418 , B23P19/10
CPC分类号： B64F5/10 , G05B19/41805
摘要： There are described herein methods and systems for manufacturing and/or assembling components having datum features thereon used to derive datum reference frames. The datum reference frames provided on the components may serve as both manufacturing and assembly datum reference frames.
摘要翻译：这里描述了用于制造和/或组装具有其上用于导出基准参考系的基准特征的部件的方法和系统。组件上提供的基准参考系可以用作制造和组装基准参考系。

28. 发明申请

WO2016049331A1 AIRCRAFT SEAT 审中-公开
标题翻译：飞机座椅
公开(公告)号：WO2016049331A1
公开(公告)日：2016-03-31
申请号：PCT/US2015/051971
申请日：2015-09-24
申请人： BOMBARDIER INC. , LEARJET INC. , ERHEL, Philippe
发明人： ERHEL, Philippe
IPC分类号： B60N2/34 , B60N2/06 , B60N2/14 , B60N2/22 , B60N2/18 , B60N2/46 , B60N2/48 , B60N2/66 , B60N2/00 , B60N2/02 , B64D11/06
CPC分类号： B60N2/002 , B60N2/028 , B60N2/06 , B60N2/062 , B60N2/14 , B60N2/1835 , B60N2/22 , B60N2/2222 , B60N2/34 , B60N2/66 , B60N2/793 , B60N2/838 , B64D11/06395 , B64D11/0641 , Y02T50/46
摘要： A seat for a vehicle includes a seat pan with a front edge defining a first pivot point and a rear edge defining a second pivot point, a backrest with a backrest bottom edge articulately disposed adjacent to the seat pan rear edge, and a headrest with a headrest bottom edge articulately disposed adjacent to the backrest top edge. The seat pan, the backrest, and the headrest are positionable with respect to one another such that the seat is configurable into at least one of a taxi, takeoff and landing position, a napping position, and a sleeping position. The first pivot point remains in a substantially fixed position for the taxi, takeoff and landing position, the sleeping position, and the napping position.
摘要翻译：一种用于车辆的座椅包括座板，其具有限定第一枢转点的前边缘和限定第二枢转点的后边缘，靠背与靠背底部边缘相邻地靠近座垫后边缘设置的头枕，以及具有头枕底部边缘靠近靠背顶部边缘铰接地设置。座椅盘，靠背和头枕可相对于彼此定位，使得座椅可配置成出租车，起飞和着陆位置，起床位置和睡眠位置中的至少一个。第一枢轴点对于出租车，起飞和着陆位置，睡眠位置和起床位置保持基本上固定的位置。

29. 发明申请

WO2015170233A1 A METHOD AND SYSTEM FOR QUANTIFYING THE IMPACT OF FEATURES ON COMPOSITE COMPONENTS 审中-公开
标题翻译：一种量化复合材料特征影响的方法和系统
公开(公告)号：WO2015170233A1
公开(公告)日：2015-11-12
申请号：PCT/IB2015/053175
申请日：2015-04-30
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： MAROUZE, Jean-philippe , KASSIE, Vishal , LALIBERTE, Jonathan , CROFT, Kaven
IPC分类号： G05B19/4097
CPC分类号： G06F17/5009 , G05B19/4097 , G05B2219/45238 , G06F2217/12 , Y02P90/265
摘要： There is described herein a process for assigning location-specific correction factors to composite components using data obtained from the simulation of an automated manufacturing process, and correlating the location-specific correction factors to safety margins across the surface of the composite component, in order to quantify the impact of features introduced by the manufacturing process.
摘要翻译：这里描述了使用从自动化制造过程的模拟获得的数据将位置特定校正因子分配给复合部件的过程，并且将位置特定校正因子与复合部件的表面上的安全裕度相关联，以便量化制造过程引入的功能的影响。

30. 发明申请

WO2015162542A2 BUFFER ZONE FOR INTERIOR AIRCRAFT FEATURES 审中-公开
标题翻译：缓冲区内部飞机特点
公开(公告)号：WO2015162542A2
公开(公告)日：2015-10-29
申请号：PCT/IB2015/052876
申请日：2015-04-20
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： MALEK, Bruce , HOLOWKA, Stefan , BEAUDIN, Nikolas
IPC分类号： B64C1/06
CPC分类号： B64C1/066 , B64C1/10 , B64D11/0023 , B64D2011/0046 , B64F5/10
摘要： Several embodiments of buffer zones are provided that are contemplated to be disposed with respect to two or more adjacent elements on an aircraft. The buffer zones adjust for dynamic spacing between the elements to help control different gapping requirements between the elements installed in the aircraft. Embodiments include an aircraft interior panel configuration, an aircraft interior wall panel configuration, an adjustable width aircraft bulkhead, and an aircraft personal service unit.
摘要翻译：提供缓冲区的几个实施例，其被设想为相对于飞行器上的两个或更多个相邻元件设置。缓冲区可调节元件之间的动态间距，以帮助控制安装在飞机上的元件之间的不同间隙要求。实施例包括飞行器内部面板配置，飞行器内部壁板配置，可调节宽度的飞行器舱壁和飞行器个人服务单元。

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