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31. 发明申请

US20150325353A1 Redundant Current-Sum Feedback Actuator 有权
标题翻译：冗余电流和反馈执行器
公开(公告)号：US20150325353A1
公开(公告)日：2015-11-12
申请号：US14803392
申请日：2015-07-20
申请人： The Boeing Company
发明人： Gen Matsui
IPC分类号： H01F7/06 , B64C13/16 , B64C13/50
CPC分类号： H01F7/064 , B64C13/16 , B64C13/42 , B64C13/50 , B64C13/503 , B64C13/504 , B64C19/00
摘要： A system and methods for redundant current-sum feedback control of an actuator system is presented. An actuator comprises actuation coils configured to actuate the actuator, and an actuation coil current sensor senses a measured total coil current comprising a sum of coil currents of each of the actuation coils. Actuator coil controllers control the actuation coils based on a commanded total coil current and the measured total coil current.
摘要翻译：提出了一种用于执行器系统的冗余电流和反馈控制的系统和方法。致动器包括构造成致动致动器的致动线圈，并且致动线圈电流传感器感测测量的总线圈电流，其包括每个致动线圈的线圈电流之和。执行机构线圈控制器根据指令的总线圈电流和测得的总线圈电流来控制驱动线圈。

32. 发明申请

US20150252869A1 DISENGAGEABLE DAMPING ASSEMBLIES FOR MOVING AERODYNAMIC SURFACES 审中-公开
标题翻译：用于移动空气动力学表面的可消除阻尼组件
公开(公告)号：US20150252869A1
公开(公告)日：2015-09-10
申请号：US14639283
申请日：2015-03-05
申请人： Goodrich Actuation Systems SAS
发明人： Serge Grand , Serge Bloch
IPC分类号： F16F15/03 , B64C13/50 , H02K49/04
CPC分类号： F16F15/035 , B64C13/50 , B64D45/00 , B64D2045/0085 , H02K49/043
摘要： A damping assembly is described herein for use in a device having moving aerodynamic surfaces including a first component comprising a back iron and at least one permanent magnet, said at least one permanent magnet providing a first magnetic field, and an electrically conductive second component, said electrically conductive second component and said first component being positioned coaxially about a central axis with said at least one permanent magnet being positioned between said back iron of said first component and said electrically conductive second component; the assembly further comprising means for rotating one or both of said at least one permanent magnet of said first component and said electrically conductive second component about said central axis to cause relative rotational movement between the at least one permanent magnet and second component, to thereby induce a variable magnetic flux in said electrically conductive second component and cause eddy currents to develop.
摘要翻译：本文描述了一种用于具有运动的空气动力学表面的装置的阻尼组件，包括包括后铁和至少一个永磁体的第一部件，所述至少一个永磁体提供第一磁场，以及导电的第二部件，所述第二部件导电的第二部件和所述第一部件围绕中心轴同轴地定位，所述至少一个永磁体位于所述第一部件的所述后铁和所述导电的第二部件之间; 所述组件还包括用于使所述第一部件的所述至少一个永磁体中的一个或两个绕所述中心轴旋转的装置，以在所述至少一个永磁体和第二部件之间产生相对的旋转运动，从而诱导在所述导电的第二部件中的可变磁通量并引起涡流的发展。

33. 发明申请

US20150217855A1 CONTROL SURFACE ACTUATION ASSEMBLY 审中-公开
标题翻译：控制面执行装置
公开(公告)号：US20150217855A1
公开(公告)日：2015-08-06
申请号：US14420366
申请日：2013-08-12
申请人： MOOG WOLVERHAMPTON LIMITED
发明人： Jonathan Davies
IPC分类号： B64C13/50 , G01M17/04 , B64C13/34
CPC分类号： B64C13/505 , B64C13/50 , F16H1/46 , F16H2001/2872 , F16H2001/2881 , G01M17/04 , Y02T50/44
摘要： An aircraft control surface actuation assembly comprises a first electromechanical actuator assembly (44) driven by two independent motors (48, 50) for redundancy, with a damping assembly (46) provided to mitigate flutter.
摘要翻译：飞行器控制表面致动组件包括由用于冗余的两个独立的马达（48,50）驱动的第一机电致动器组件（44），其中设置有用于减轻颤振的阻尼组件（46）。

34. 发明申请

US20150083853A1 ADAPTIVE TRAILING EDGE ACTUATOR SYSTEM AND METHOD 有权
标题翻译：自适应跟踪边缘执行器系统和方法
公开(公告)号：US20150083853A1
公开(公告)日：2015-03-26
申请号：US14034946
申请日：2013-09-24
申请人： THE BOEING COMPANY
发明人： Matthew A. Moser , Michael R. Finn
IPC分类号： B64C13/50
CPC分类号： B64C13/50 , B64C9/16 , B64C13/28 , B64C2003/145 , Y02T50/12 , Y02T50/32
摘要： An adaptive trailing edge system for an aircraft may include an adaptive trailing edge element mounted to a trailing edge. An electric motor actuator having an electric motor may be configured to actuate the adaptive trailing edge element. A linkage system may couple the electric motor actuator to the adaptive trailing edge element for actuation thereof.
摘要翻译：用于飞行器的自适应后缘系统可以包括安装到后缘的自适应后缘元件。具有电动机的电动机致动器可被配置为致动自适应后缘元件。联动系统可以将电动机致动器耦合到自适应后缘元件以用于其致动。

35. 发明授权

US08789791B2 Electrical system and electrical accumulator for electrical actuation and related methods 有权
标题翻译：电气系统和蓄电池用于电气驱动及相关方法
公开(公告)号：US08789791B2
公开(公告)日：2014-07-29
申请号：US12136652
申请日：2008-06-10
申请人： Anthony F. Matasso , Steven M. Iden
发明人： Anthony F. Matasso , Steven M. Iden
IPC分类号： B64C13/50
CPC分类号： B64C13/50 , B64D2221/00 , H02J1/10 , Y02T50/44 , Y02T50/54
摘要： An electrical system for driving flight control actuators, electrical accumulator, and methods for managing electrical power for an aircraft electrical system and methods of retrofitting an aircraft electrical system with an electrical accumulator are provided. The electrical system can include a bidirectional accumulator positioned in electrical communication with the plurality of flight control actuators to absorb excess electrical power regenerated by the plurality of flight control actuators and to provide supplemental power to the plurality of flight control actuators to thereby satisfy transient power requirements.
摘要翻译：提供了一种用于驱动飞行控制致动器，蓄电器和用于管理飞机电气系统的电力的方法的电气系统以及使用蓄电器改装飞行器电气系统的方法。电气系统可以包括位于与多个飞行控制致动器电连通的双向蓄能器，以吸收由多个飞行控制致动器再生的多余电力，并向多个飞行控制致动器提供补充功率，从而满足瞬时功率要求。

36. 发明授权

US08698444B2 Aircraft electrical actuator arrangement 有权
标题翻译：飞机电动执行器装置
公开(公告)号：US08698444B2
公开(公告)日：2014-04-15
申请号：US12731642
申请日：2010-03-25
申请人： Peter Malkin , David R Trainer
发明人： Peter Malkin , David R Trainer
IPC分类号： H02P8/00 , H02P7/00 , B64C17/00 , F16K31/02
CPC分类号： B64C13/28 , B64C13/50 , H02J3/14 , Y02T50/44
摘要： An aircraft electrical actuator arrangement includes a plurality of actuators and a master power converter to convert power from the electrical power distribution network for supply to each actuator. The actuators include an environmental control system actuator, an aileron actuator, a flap actuator, a slat actuator, a landing gear actuator, a thrust reverser actuator, a brake actuator and a taxiing actuator. A controller is coupled to the master power converter and is arranged to allow the supply of power from the master power converter to the environmental control system actuator during a first mode of operation of the aircraft. The controller is arranged to allow the supply of electrical power from the master power converter to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator during a second mode of operation of the aircraft.
摘要翻译：飞行器电动执行器装置包括多个致动器和主功率转换器，用于将来自配电网络的功率转换成每个致动器。执行器包括环境控制系统致动器，副翼致动器，翼片致动器，板条致动器，起落架致动器，推力反向器致动器，制动致动器和滑行致动器。控制器耦合到主功率转换器，并且被布置成允许在飞行器的第一操作模式期间从主功率转换器向环境控制系统致动器供电。控制器被布置成允许在第二模式期间将来自主功率转换器的电力供应到副翼，翼片，板条，起落架，推力反向器，制动致动器或滑行致动器中的至少一个飞机的运行。

37. 发明申请

US20140027580A1 HIGH LIFT SYSTEM FOR AN AIRCRAFT 有权
标题翻译：用于飞机的高起升系统
公开(公告)号：US20140027580A1
公开(公告)日：2014-01-30
申请号：US14044960
申请日：2013-10-03
申请人： Airbus Operations GmbH
发明人： Markus Christmann , Christoph Giebeler , Martin Recksiek , Bjoern Dorr
IPC分类号： B64C3/50 , H02K3/28
CPC分类号： B64C3/50 , B64C9/16 , B64C9/22 , B64C13/24 , B64C13/50 , H02K3/28 , Y02T50/44
摘要： A high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor.
摘要翻译：用于飞机的高升力系统，其以完全电动的方式延伸和缩回飞机的着陆翼。在这种情况下，使用全电驱动器，其包括具有内部冗余的电动机，使得电动机被配置为容错电动机。因此，可以在电动机中没有联接齿轮单元的情况下进行。

38. 发明申请

US20130334372A1 METHOD OF OPERATING ACTUATORS SIMULTANEOUSLY FOR MOVING AIRCRAFT FLAPS, AN AIRCRAFT FLAP DRIVE DEVICE, AND AN AIRCRAFT PROVIDED WITH SUCH A DEVICE 有权
标题翻译：同时操作执行机构的方法，用于移动飞机飞行器，飞机飞行器驱动装置以及提供有该装置的飞机
公开(公告)号：US20130334372A1
公开(公告)日：2013-12-19
申请号：US14002062
申请日：2012-02-29
申请人： Frederic Marques , Guillaume Mercier , Stephane Menio
发明人： Frederic Marques , Guillaume Mercier , Stephane Menio
IPC分类号： B64C13/16
CPC分类号： B64C13/16 , B64C13/50 , B64C13/503 , B64D45/00 , B64D2045/001
摘要： A method of operating actuators simultaneously for moving at least two aircraft movable aerodynamic surfaces, the method comprising the steps of: controlling the actuators to move the aerodynamic surfaces towards a predetermined position; during the movement, detecting a slowest actuator; and adapting the control of the actuators to match the actions of the slowest actuator. A drive device for aerodynamic surfaces and an aircraft including such a device.
摘要翻译：一种同时操作致动器的方法，用于移动至少两个飞行器可移动空气动力学表面，该方法包括以下步骤：控制致动器将空气动力学表面朝向预定位置移动; 在运动期间，检测到最慢的执行器; 并适应致动器的控制以匹配最慢致动器的动作。用于空气动力学表面的驱动装置和包括这种装置的飞行器。

39. 发明申请

US20130213160A1 ELECTRO MECHANICAL ACTUATOR 有权
标题翻译：电动机械执行器
公开(公告)号：US20130213160A1
公开(公告)日：2013-08-22
申请号：US13762588
申请日：2013-02-08
申请人： EADS CONSTRUCCIONES AERONAUTICAS S. A.
发明人： Santiago Flores Giraldo , Francisco Javier Fernandez Garcia
IPC分类号： F16H19/04
CPC分类号： F16H19/04 , B64C13/42 , B64C13/50 , F16H2057/0081 , F16H2057/018 , Y02T50/44 , Y02T50/54 , Y10T74/18096
摘要： A two-stage linear actuator particularly applicable to aircraft control surfaces. The first stage comprises a rotary input shaft driven by an electric motor having a helical threaded zone in its external surface at its inner end and a plurality of first helical roller gears configured to engage with the rotary input shaft in its helical threaded zone for rotating together. The second stage comprises a plurality of second helical roller gears configured to engage with the first helical roller gears for rotating together and with an output shaft having a helical threaded zone in its external surface at its inner end for converting the rotation of the second helical roller gears in a linear movement of the output shaft.
摘要翻译：特别适用于飞机控制面的两级线性执行机构。第一级包括由电动机驱动的旋转输入轴，其在其内端处的外表面具有螺旋形螺纹区域，以及多个第一螺旋形滚子齿轮，其构造成与旋转输入轴接合在其螺旋螺纹区域中以一起旋转。第二级包括多个第二螺旋滚子齿轮，其构造成与第一螺旋滚子齿轮啮合，用于一起旋转，并且其输出轴在其外表面具有螺旋形螺纹区域，用于转换第二螺旋辊输出轴线性移动的齿轮。

40. 发明申请

US20120193183A1 SHAPE MEMORY ALLOY ACTUATED TORSION LOCK 有权
标题翻译：形状记忆合金启动扭矩锁
公开(公告)号：US20120193183A1
公开(公告)日：2012-08-02
申请号：US13019973
申请日：2011-02-02
申请人： Ian M. Gunter , Dan Clingman
发明人： Ian M. Gunter , Dan Clingman
IPC分类号： F16D21/00 , F16D11/14 , F16D11/00
CPC分类号： B64C9/16 , B64C9/22 , B64C9/323 , B64C13/50 , B64C2003/145 , F03G7/065 , F16D43/25 , Y02T50/12 , Y02T50/32
摘要： A torsion lock may include a clutch, a spring, and a shape memory alloy (SMA) member. The spring may cause the application of pressure on the clutch for engagement thereof. The SMA member may linearly contract when heated in a manner to relieve the pressure on the clutch for disengagement thereof.
摘要翻译：扭转锁可以包括离合器，弹簧和形状记忆合金（SMA）构件。弹簧可能导致对离合器施加压力以进行接合。当加热时，SMA构件可以线性地收缩，以减轻离合器上的压力以使其脱离。

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