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11. 发明公开

EP2915744A1 Flight control actuator drive 有权转让
标题翻译： AktuatorantriebfürFlugsteuerung
公开(公告)号：EP2915744A1
公开(公告)日：2015-09-09
申请号：EP14305310.6
申请日：2014-03-05
申请人： Goodrich Actuation Systems SAS
发明人： Grand, Serge
IPC分类号： B64C13/34 , F16H1/36
CPC分类号： B64C13/34 , B64C13/42 , B64C13/50 , F16H1/36 , F16H37/0826
摘要： A flight control actuator drive (100) comprises a first motor (10) for providing a first rotational input, a second motor (12) for providing a second rotational input and a speed summing device (20) for combining the first and second rotational inputs into a rotational output for controlling an actuator. The speed summing device (20) comprises first and second input gears (22, 24) to which the first and second motors (10, 12) are connected via first and second irreversible gears (14, 16) so that the first and second input gears (22, 24) can each transmit power in one direction only. The speed summing device (20) may be a planetary gear assembly.
摘要翻译：飞行控制致动器驱动器（100）包括用于提供第一旋转输入的第一马达（10），用于提供第二旋转输入的第二马达（12）和用于组合第一和第二旋转输入的速度求和装置（20）成为用于控制致动器的旋转输出。速度求和装置（20）包括第一和第二输入齿轮（22,24），第一和第二马达（10,12）经由第一和第二不可逆齿轮（14,16）连接到第一和第二输入齿轮（22,24），使得第一和第二输入齿轮（22,24）可以仅在一个方向上传递动力。速度求和装置（20）可以是行星齿轮组件。

12. 发明授权

EP2501483B1 DUAL-PATH FLUID INJECTION JET 有权
标题翻译：双路径流体喷射
公开(公告)号：EP2501483B1
公开(公告)日：2015-08-19
申请号：EP09851340.1
申请日：2009-11-16
申请人： Bell Helicopter Textron Inc.
发明人： POSTER, Scott
IPC分类号： B05B7/00 , B05B7/08
CPC分类号： F16N7/40 , B05B1/16 , B05B1/20 , B05B7/08 , B05B9/002 , B05B9/0409 , B05B9/0423 , B05B14/00 , B05B15/62 , B64C13/42 , F01M2005/028 , F16H57/0456 , F16N17/00 , F16N2260/24 , Y10T137/85954
摘要： An injection jet (437) includes a body (601) having a first (701) and a second (703) passage disposed therein for channeling a fluid to a working element (303). The first passage (701) remains fluidly separated from the second passage (703). A system includes the injection jet (437) along with a main reservoir (405) and an emergency reservoir (415). The first passage (701) is in fluid communication with the main reservoir (405), while the second passage (703) is in fluid communication with the emergency reservoir (415). The system operates in a standard mode and an emergency mode. Both the first passage (701) and the second passage (703) are configured for jointly supplying fluid to the working element during standard mode. The second passage is configured for independently supplying fluid to the working element (303) during emergency mode.

13. 发明公开

EP2867119A1 ZONAL HYDRAULIC SYSTEMS AND METHODS 有权
标题翻译： ZONALE HYDRAULIKSYSTEME UNDOVERHREN
公开(公告)号：EP2867119A1
公开(公告)日：2015-05-06
申请号：EP13734903.1
申请日：2013-06-20
申请人： Eaton Corporation
发明人： HANSEN, Nicholas, John , JONES, Joseph, Matthew , BENAWAY, Barry
IPC分类号： B64C13/42 , F15B11/17
CPC分类号： B64C13/42 , F15B11/17 , F15B20/00 , F15B20/004 , F15B2211/20576 , F15B2211/30505 , F15B2211/30565 , F15B2211/3138 , F15B2211/31535 , F15B2211/329 , F15B2211/355 , F15B2211/8633 , F15B2211/8752 , Y10T137/87209
摘要： The present disclosure relates to isolation and reconfiguration schemes, architectures and methods for use in aircraft hydraulic systems. The main hydraulic system of each hydraulic section of the aircraft hydraulic system can be isolated from one or more consumers in the event of a leak without the use pressure from the backup system. Further, in some embodiments, the main hydraulic system of each hydraulic section of the aircraft hydraulic system can be isolated from one or more consumers in the event of a leak without the use pressure from the backup system and the main system.
摘要翻译：本公开涉及用于飞行器液压系统的隔离和重新配置方案，架构和方法。在没有来自备用系统的使用压力的情况下，飞机液压系统的每个液压部分的主液压系统可以与一个或多个消费者隔离。此外，在一些实施例中，在没有来自备用系统和主系统的使用压力的情况下，飞行器液压系统的每个液压部分的主液压系统可以与一个或多个使用者隔离。

14. 发明公开

EP2576340A2 A DEVICE FOR AN ADJUSTABLE FLAP OF A WING 审中-公开
标题翻译： DEVICE一个侧翼球员可定制的舵
公开(公告)号：EP2576340A2
公开(公告)日：2013-04-10
申请号：EP11722330.5
申请日：2011-05-26
申请人： Airbus Operations GmbH
发明人： DYCKRUP, Werner , ELLMERS, Wilfried
IPC分类号： B64C9/02 , B64C9/16 , B64C13/42
CPC分类号： B64C13/28 , B64C9/02 , B64C9/16 , B64C13/42 , B64D2045/001 , Y02T50/44
摘要： The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator (13) arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism (15) running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. In the device at least one damping unit (16) for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which in particular can be brought about as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap.

15. 发明公开

EP1964771A3 Load optimized redundant flight control surface actuation system and method 审中-公开
标题翻译：负荷最优化冗余飞行器操纵面驱动系统和方法
公开(公告)号：EP1964771A3
公开(公告)日：2012-01-18
申请号：EP08102039.8
申请日：2008-02-26
申请人： Honeywell International Inc.
发明人： Yount, Larry J. , Hanlon, Casey , Johnson, Andy , Jackson, Joe
IPC分类号： B64C13/42
CPC分类号： B64C13/42 , Y02T50/44
摘要： An aircraft flight surface control system and method simultaneously provides the benefits of both an active/active system architecture and an active/standby system architecture. The system is preferably implemented using hydraulic actuator assemblies (202H,204H,206H) and electromechanical actuator assemblies (202E,204E,206E) coupled to the same flight control surface. During normal system operations the electromechanical actuator assemblies are energized to supply a relatively minimal force to associated flight control surfaces. In effect, the electromechanical actuators, although energized, may be pulled along by the associated hydraulic actuator assemblies, until needed. Thus, the electromechanical actuator assemblies are controlled in a manner that closely resembles the active/standby architecture.

16. 发明公开

EP2383181A2 Hydraulic apparatus for aircraft actuators 有权
标题翻译： HydraulikvorrichtungfürFlugzeugbetätiger
公开(公告)号：EP2383181A2
公开(公告)日：2011-11-02
申请号：EP11164151.0
申请日：2011-04-28
申请人： Nabtesco Corporation
发明人： Nakagawa, Shingo , Fukui, Atsushi
IPC分类号： B64C13/40 , B64C13/50
CPC分类号： B64C13/40 , B64C13/42 , F15B2211/20515 , F15B2211/20576 , F15B2211/62 , F15B2211/8633 , Y02T50/44
摘要： A pump unit (12) installed inside a wing (100), and a panel body (11) constituting part of a wing structure portion forming a surface structure of the wing (100) are provided. The pump unit (12) includes a backup hydraulic pump (13) that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor (14) that drives this pump. Except for at least the panel body, the wing structure portion is formed from fiber reinforced plastics. The panel body (11) is formed of a metallic material.
摘要翻译：设置在机翼（100）内的泵单元（12）和构成机翼（100）的表面结构的机翼结构部分的一部分的面板体（11）。泵单元（12）包括备用液压泵（13），当在飞行器中央液压动力源和驱动该泵的电动机（14）的功能中发生损失或减少时，能够向致动器供应压力油。除了至少面板主体之外，翼结构部分由纤维增强塑料形成。面板主体（11）由金属材料形成。

17. 发明公开

EP2343613A2 Flight control system 有权
标题翻译：飞行控制系统
公开(公告)号：EP2343613A2
公开(公告)日：2011-07-13
申请号：EP10176344.9
申请日：2010-09-13
申请人： Nabtesco Corporation
发明人： Nakagawa, Shingo , Kojima, Satoru
IPC分类号： G05D1/00
CPC分类号： G05D1/0055 , B64C13/42 , B64C13/503
摘要： A flight control system (100) for an aircraft includes a PCS (1) generating a pilot control signal based on pilot operations of a stick control and others, an FCC (2) for controlling flight control surfaces of the aircraft, a surface control device (4) arranged for each flight control surface (5) to control it based on a surface control signal transmitted from the FCC, and a data bus (3) for connecting the FCC and the surface control device. The surface control device includes an ACE (6) executing servo calculation process and outputting an actuator operation signal, and an actuator section (7) for controlling hydraulic oil supplied to a hydraulic cylinder based on the actuator operation signal. A single flight control surface is controlled by a plurality of ACE and actuator section pairs, and the ACE includes a normal control section (62), a monitoring section (63), a backup control section (64), and the like.

18. 发明公开

EP2263012A1 HYDRAULIC ACTUATOR WITH FLOATING PISTONS 有权
标题翻译：游泳活塞液压机构
公开(公告)号：EP2263012A1
公开(公告)日：2010-12-22
申请号：EP08873340.7
申请日：2008-11-26
申请人： Woodward HRT, Inc.
发明人： FENNY, Carlos, A. , KINARD, Marc, W. , LAUFFER, John
IPC分类号： F15B15/14 , F15B20/00
CPC分类号： H03C1/34 , B64C13/42 , F15B2211/20576 , F15B2211/31535 , F15B2211/324 , F15B2211/7054 , F15B2211/7055 , F15B2211/7056 , F15B2211/7107 , F15B2211/8757 , H03C7/00 , Y02T50/44 , Y10T137/86606
摘要： A hydraulic actuator is configured to provide redundant boost control to an aircraft within approximately the same space required by a single hydraulic cylinder. The hydraulic actuator includes a housing and a piston assembly disposed within the housing. The piston assembly includes a ram, a first piston secured to the ram, and second and third pistons disposed on the ram such that the second and third pistons are translatable relative to the longitudinal axis pf the ram. The pistons form two hydraulically separate actuator cylinders within the space required by a single cylinder which results in a reduction in the weight and size of the hydraulic actuator.

19. 发明授权

EP1700041B1 REDUNDANT FLOW CONTROL FOR HYDRAULIC ACTUATOR SYSTEMS 有权转让
标题翻译：冗余流量控制致动器的液压系统
公开(公告)号：EP1700041B1
公开(公告)日：2010-10-27
申请号：EP04822162.6
申请日：2004-12-01
申请人： Woodward HRT, Inc.
发明人： HART, Kenneth, E.
IPC分类号： F15B20/00 , B64C13/42 , F15B18/00
CPC分类号： F15B13/0403 , B64C13/42 , F15B15/1404 , F15B18/00 , F15B20/004 , F15B20/008 , F15B2211/30525 , F15B2211/7056 , F15B2211/8633 , F15B2211/8636 , F15B2211/864 , F15B2211/8757
摘要： Two or more flow control valves (140a, 140b) may be used to provide redundant flow control for a hydraulic actuator (111) or servoactuator. The flow control valves include a sleeve (142a, 142b) control spool (146a, 146b). Under normal operating conditions, each bypass control spool is stationary relative to the sleeve and the flow control valve functions as a four-way hydraulic flow control valve. Each flow control valve is connected to a bypass-shutoff valve (160a, 160b) including a bypass spool that is moveable from a shut-off position to a bypass position. Upon supply pressure failure to one flow control valve, the bypass spool moves to the bypass position, reducing pressure in the corresponding actuator piston chambers. When a primary control spool (146a, 146b) becomes jammed, the corresponding bypass control spool moves within its sleeve (142a, 142b) allowing a bypass groove to port control pressure to the return line, thereby reducing pressure in the corresponding actuator piston chambers.

20. 发明公开

EP1803644A3 Distributed flight control surface actuation system 有权
标题翻译：分布式操作系统的飞机控制面
公开(公告)号：EP1803644A3
公开(公告)日：2008-05-21
申请号：EP06126591.4
申请日：2006-12-20
申请人： Honeywell International Inc.
发明人： Johnson, Andrew T. , Hanlon, Casey , Potter, Calvin C.
IPC分类号： B64C13/50
CPC分类号： B64C13/50 , B64C13/42
摘要： An aircraft flight control surface actuation system (110) includes a plurality of flap actuators (112), and a plurality of slat actuators (114). The actuators receive actuator position commands from an actuator control unit (124) and, in response, move flaps (102) and slats (104) between stowed and deployed positions. The flight control surface actuator control unit (124) includes a plurality of independent actuator control channels. One or more of the independent actuator control channels (126-1, 126-2, 126-3, 126-4, 126-5) is coupled to both a flap actuator (112) and a slat actuator (114), and is configured to selectively supply the actuator position commands thereto.

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