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1. 发明公开

EP3318493A1 TRANSMISSION OF POWER AND COMMUNICATION OF SIGNALS OVER FUEL AND HYDRAULIC LINES IN A VEHICLE 审中-公开
标题翻译：车辆内燃料和液压管路的动力传输和信号通信
公开(公告)号：EP3318493A1
公开(公告)日：2018-05-09
申请号：EP17199882.6
申请日：2017-11-03
申请人： GE Aviation Systems LLC
发明人： BOBREK, Pavlo , GARDNER, Eric Rankin
IPC分类号： B64D31/14 , B64D37/00 , B64C13/36 , B64C13/40 , H01Q1/46 , G08B1/06 , G08C23/00 , H04B13/00
CPC分类号： B64C13/36 , B64C13/40 , B64D31/14 , B64D37/00 , G08B1/06 , G08C23/00 , H01Q1/46 , H04B13/00 , Y02T50/44
摘要： Systems 600 and methods 700 for communicating a signal over a hydraulic line 620 in a vehicle 10 are provided. In one embodiment, a system 600 can include a hydraulic line 620. The hydraulic line 620 can include at least one communication medium for propagating a communication signal. The system 600 can also include at least one signal communication device 140 configured to receive the communication signal communicated over the hydraulic line 620. The system 600 can also include at least one vehicle component 450 in communication with the at least one signal communication device 140.
摘要翻译：提供了用于在车辆10中的液压管线620上传送信号的系统600和方法700。在一个实施例中，系统600可以包括液压管线620.液压管线620可以包括用于传播通信信号的至少一个通信介质。系统600还可以包括至少一个信号通信装置140，该信号通信装置140被配置为接收通过液压管线620传送的通信信号。系统600还可以包括与至少一个信号通信装置140通信的至少一个车辆部件450。

2. 发明公开

EP2939921A1 LEADING EDGE ASSEMBLY FOR AN AIRCRAFT 有权
标题翻译：一个平面前角安排
公开(公告)号：EP2939921A1
公开(公告)日：2015-11-04
申请号：EP15163137.1
申请日：2015-04-10
申请人： The Boeing Company
发明人： Smith, Clayton A
IPC分类号： B64C9/22
CPC分类号： B64C9/34 , B64C9/22 , B64C13/36 , B64C2009/143 , Y02T50/32
摘要： A wing assembly includes a main wing (500) and a slat (510) movable between stowed and deployed positions. The main wing (500) includes a panel (512) movable to a retracted position when the slat (510) is in the stowed position, such that the slat outer surface (514) and a wing upper surface (503) define a first continuous outer mold line shape. The panel (512) may further be movable to an extended position when the slat (510) is in the deployed position, such that an outer surface (525) of the panel (512) and the wing upper surface (503) define a second continuous outer mold line shape.

3. 发明公开

EP2843243A1 Systems and methods for heat balance and transport for aircraft hydraulic systems 有权
标题翻译：系统与软件系统
公开(公告)号：EP2843243A1
公开(公告)日：2015-03-04
申请号：EP14172816.2
申请日：2014-06-17
申请人： The Boeing Company
发明人： Liao, Jianmin
IPC分类号： F15B18/00 , F15B21/04 , B64C13/36 , B64C25/22
CPC分类号： F15B21/042 , B64C13/36 , B64C13/42 , B64C25/22 , F15B1/26 , F15B2211/20576 , F15B2211/611 , F15B2211/62
摘要： A thermal management system is provided. The thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature, a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature, and a heat exchanger coupling the first hydraulic system to the second hydraulic system, wherein the heat exchanger is configured to exchange heat between the first hydraulic fluid and the second hydraulic fluid.
摘要翻译：提供热管理系统。热管理系统包括用于在第一温度下循环第一液压流体的第一液压系统，用于在高于第一温度的第二温度下循环第二液压流体的第二液压系统，以及将第一液压系统到第二液压系统，其中热交换器被配置为在第一液压流体和第二液压流体之间交换热量。

4. 发明授权

EP0465282B1 Vérin rotatif à billes 失效
标题翻译： Kugeldrehantrieb。
公开(公告)号：EP0465282B1
公开(公告)日：1994-08-24
申请号：EP91401522.7
申请日：1991-06-10
申请人： RATIER-FIGEAC
发明人： Bousquet, Jacques
IPC分类号： F15B15/08 , F16H25/22 , B64C13/36
CPC分类号： F15B15/068 , B64C13/36 , F16H25/2233 , Y10T74/18984 , Y10T74/19786

5. 发明公开

EP3367070A1 APPARATUS, SYSTEM, AND METHOD FOR DETERMINING A POSITION OF A PART 有权
公开(公告)号：EP3367070A1
公开(公告)日：2018-08-29
申请号：EP17204353.1
申请日：2017-11-29
申请人： The Boeing Company
发明人： KNOWLES, Devin E.
IPC分类号： G01D5/249
CPC分类号： G01D5/2451 , B64C9/14 , B64C13/24 , B64C13/28 , B64C13/36 , B64C2009/005 , B64D45/0005 , G01D5/2497
摘要： Disclosed herein is an apparatus for determining a position of a first part relative to a second part. The first part is movable relative to the second part. The apparatus comprises a magnetic position indicator and a magnetic field sensor. The magnetic position indicator is non-movably fixed to the first part and comprises a plurality of magnetic field sources positioned along a length of the magnetic position indicator. Each magnetic field source of the plurality of magnetic field sources generates a magnetic field having a unique magnetic signature. The magnetic field sensor is non-movably fixed to the second part and configured to detect the unique magnetic signatures of the magnetic fields generated by the plurality of magnetic field sources of the magnetic position indicator.

6. 发明授权

EP3091646B1 LINEAR ELECTROMECHANICAL ACTUATORS 有权
公开(公告)号：EP3091646B1
公开(公告)日：2018-07-25
申请号：EP16168736.3
申请日：2016-05-09
申请人： Sikorsky Aircraft Corporation
发明人： HIMMELMANN, Richard A.
IPC分类号： H02K41/03 , H02K16/00
CPC分类号： H02K41/02 , B64C13/36 , B64C13/503 , H02K11/21 , H02K16/00 , H02K41/031
摘要： An actuator (100) includes a plurality of linear motors (102). A carriage (104) is operatively connected to each linear motor to be driven by each of the linear motors. An output forcer rod (110) is operatively connected to at least one of the linear motors to be driven by at least one of the linear motors. A position sensor is operatively connected to the output forcer rod to measure motion of the output forcer rod. A fly-by-wire system (103) includes a plurality of electromechanical actuators. Each electromechanical actuator includes a plurality of linear motors. A flight control computer (105) is operatively connected to the linear motors of each of the electromechanical actuators. The fly-by-wire system includes a plurality of hydraulic systems (101). Each hydraulic system is operatively coupled to a respective one of the electromechanical actuators.

7. 发明公开

EP0465282A1 Vérin rotatif à billes 失效
标题翻译： Kugeldrehantrieb。
公开(公告)号：EP0465282A1
公开(公告)日：1992-01-08
申请号：EP91401522.7
申请日：1991-06-10
申请人： RATIER-FIGEAC
发明人： Bousquet, Jacques
IPC分类号： F15B15/08 , F16H25/22 , B64C13/36
CPC分类号： F15B15/068 , B64C13/36 , F16H25/2233 , Y10T74/18984 , Y10T74/19786
摘要： Ce vérin rotatif à billes comprend un piston (106) monté dans un corps (102, 104), le piston (106) comporte des rampes hélicoïdales (110) coopérant par l'intermédiaire de premières billes (109) avec des rampes hélicoïdales (108) formées à l'intérieur de ladite première partie (102) du corps, et des rampes rectilignes (113) coopérant par l'intermédiaire de secondes billes (112) avec des rampes rectilignes (111) formées à l'intérieur de ladite seconde partie (104); les premières billes (109) et secondes billes (112) sont maintenues respectivement dans des première (122) et seconde (125) cages à billes interposées entre le piston (106) et le corps (102, 104), asservies au mouvement du piston (106), par l'intermédiaire d'un dispositif à ergot (127, 130) et rampe hélicoïdale. Les deux cages peuvent être réunies en une seule.
摘要翻译：该旋转滚珠致动器包括安装在主体（102,104）中的活塞（106），活塞（106）具有通过第一球（109）与形成在内部上的螺旋斜坡（108）相互作用的螺旋斜面（110）和所述第二部分（104）内部形成有直线斜面（111）的第二球（112）相互作用的直线斜面（113）。第一球（109）和第二球（112）分别保持在介于活塞（106）和主体（102,104）之间的第一（112）和第二（125）球笼中，并受到活塞（106）通过具有销（127,130）和螺旋斜坡的装置。两个笼子可以组合成一个单一的。 ... ...

8. 发明授权

EP0270414B1 Système pour la commande des volets hypersustentateurs d'un aéronef 失效
标题翻译：飞行员飞行控制系统
公开(公告)号：EP0270414B1
公开(公告)日：1990-03-28
申请号：EP87402489.6
申请日：1987-11-04
申请人： AEROSPATIALE Société Nationale Industrielle
发明人： Bellego, Roger , Foch, Etienne
IPC分类号： B64C13/36
CPC分类号： B64D45/0005 , B64C13/36 , B64D2045/001

9. 发明公开

EP3378763A1 AIRCRAFT HYDRAULIC SYSTEMS HAVING SHARED COMPONENTS 有权
公开(公告)号：EP3378763A1
公开(公告)日：2018-09-26
申请号：EP18155552.5
申请日：2018-02-07
申请人： Bell Helicopter Textron Inc.
发明人： ELVING, Carl Theodore , REYNOLDS, Robert Paul , HAWTHORNE, David Alan , FENNY, Carlos Alexander
IPC分类号： B64C13/40 , B64D41/00 , B64C13/42 , F15B18/00 , B64C29/00 , B64C27/28
CPC分类号： F15B11/17 , B64C13/36 , B64C13/40 , B64C13/42 , B64C27/28 , B64C29/0033 , B64D29/02 , B64D41/00 , F15B1/26 , F15B2211/20576 , F15B2211/7142 , Y02T50/44
摘要： A hydraulic system (100) for an aircraft having an engine (108) and an auxiliary power unit (122) includes a first hydraulic subsystem (102) including a first hydraulic pump (106) and a first set of hydraulic-powered components (112, 114, 116) in fluid communication with the first hydraulic pump (106). The first hydraulic pump (106) is powered by the engine (108) to pump shared hydraulic fluid to the first set of hydraulic-powered components (112, 114, 116). The hydraulic system (100) includes a second hydraulic subsystem (104) including a second hydraulic pump (120) and a second set of hydraulic-powered components (126, 128, 130) in fluid communication with the second hydraulic pump (120). The second hydraulic pump (120) is powered by the auxiliary power unit (122) to pump the shared hydraulic fluid to the second set of hydraulic-powered components (126, 128, 130). A shared return line subsystem (134) and reservoir (136) is in fluid communication with the first and second hydraulic subsystems (102, 104) to return the shared hydraulic fluid to the first and second hydraulic pumps (106, 120).

10. 发明公开

EP3091646A1 LINEAR ELECTROMECHANICAL ACTUATORS 有权
标题翻译： LINEARE ELEKTROMECHANISCHE AKTUATOREN
公开(公告)号：EP3091646A1
公开(公告)日：2016-11-09
申请号：EP16168736.3
申请日：2016-05-09
申请人： Sikorsky Aircraft Corporation
发明人： HIMMELMANN, Richard A.
IPC分类号： H02K41/03 , H02K16/00
CPC分类号： H02K41/02 , B64C13/36 , B64C13/503 , H02K11/21 , H02K16/00 , H02K41/031
摘要： An actuator (100) includes a plurality of linear motors (102). A carriage (104) is operatively connected to each linear motor to be driven by each of the linear motors. An output forcer rod (110) is operatively connected to at least one of the linear motors to be driven by at least one of the linear motors. A position sensor is operatively connected to the output forcer rod to measure motion of the output forcer rod. A fly-by-wire system (103) includes a plurality of electromechanical actuators. Each electromechanical actuator includes a plurality of linear motors. A flight control computer (105) is operatively connected to the linear motors of each of the electromechanical actuators. The fly-by-wire system includes a plurality of hydraulic systems (101). Each hydraulic system is operatively coupled to a respective one of the electromechanical actuators.
摘要翻译：致动器（100）包括多个线性马达（102）。托架（104）可操作地连接到每个线性马达以由每个线性马达驱动。输出锻炼杆（110）可操作地连接到至少一个直线电动机，以由至少一个直线电动机驱动。位置传感器可操作地连接到输出锻炼杆以测量输出锻炼棒的运动。电线控制系统（103）包括多个机电致动器。每个机电致动器包括多个线性马达。飞行控制计算机（105）可操作地连接到每个机电致动器的线性马达。线控线系统包括多个液压系统（101）。每个液压系统可操作地耦合到相应的一个机电致动器。

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