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61. 发明授权

EP2944566B1 SYSTEM AND METHOD FOR OPTIMIZING HORIZONTAL TAIL LOADS 有权
标题翻译：用于优化水平尾部载荷的系统和方法
公开(公告)号：EP2944566B1
公开(公告)日：2017-11-08
申请号：EP15162586.0
申请日：2015-04-07
申请人： The Boeing Company
发明人： Mahmulyin, Vedad
IPC分类号： B64C13/16 , B64C13/50 , G05D1/00 , G05D1/08
CPC分类号： B64C13/00 , B64C5/02 , B64C9/00 , B64C13/04 , B64C13/16 , B64C13/503 , B64D43/02 , G05D1/0066
摘要： A method of controlling an elevator of an aircraft may include identifying a current stabilizer angle of incidence of a stabilizer of the aircraft. The stabilizer may include an elevator pivotably coupled to the stabilizer. The method may further include comparing the current stabilizer angle of incidence with a threshold stabilizer angle of incidence, and selecting an elevator position limit that is more restrictive if the current stabilizer angle of incidence is greater than or equal to the threshold stabilizer angle of incidence. The method may additionally include moving the elevator to a commanded elevator position that is no greater than the elevator position limit.

62. 发明公开

EP2527248A3 Suppressing electrical failure effects in servo control systems 有权
标题翻译：抑制伺服控制系统中的电气故障影响
公开(公告)号：EP2527248A3
公开(公告)日：2017-11-08
申请号：EP12169236.2
申请日：2012-05-24
申请人： The Boeing Company
发明人： Matsui, Gen
IPC分类号： B64C13/40 , B64C13/50
CPC分类号： B64C13/40 , B64C13/503
摘要： Systems to manage servo controls are disclosed. In some embodiments servo controls may implemented in systems to deflect control surfaces in aircraft. In one embodiment, a system to manage the output of a servo valve (220) comprises a first plurality of feedback loops (270) to receive a plurality of commands representative of a desired piston (252) position and to generate, from the plurality of commands, a plurality of position difference signals (315) which represent a difference between a desired piston (252) position and a current piston (252) position, a plurality of amplifiers (206, 210) to generate, from the plurality of position difference signals (315), a corresponding plurality of magnetic flux target signals (320), a second plurality of feedback loops (272) to receive, from the plurality of amplifiers (206, 210), the plurality of magnetic flux target signals (320), wherein the magnetic flux target signals (320) represent a desired magnetic flux measurement in the servo valve (220), and to generate, from the plurality of magnetic flux target signals (320), a plurality of magnetic flux difference signals (325) which represent a difference between a desired magnetic flux measurement and a current magnetic flux measurement, and an assembly to regulate the servo valve (220) using the plurality of magnetic flux target signals (320). Other embodiments may be described.
摘要翻译：披露了管理伺服控制的系统。在一些实施例中，伺服控制可以在系统中实施以偏转飞机中的控制表面。在一个实施例中，用于管理伺服阀（220）的输出的系统包括第一多个反馈回路（270），以接收代表期望活塞（252）位置的多个命令并且从多个命令，多个表示期望活塞（252）位置和当前活塞（252）位置之间的差异的位置差异信号（315），多个放大器（206,210），用于从所述多个位置差用于从所述多个放大器（206,210）接收所述多个磁通量目标信号（320）的信号（315），对应的多个磁通量目标信号（320），第二多个反馈回路（272）其中，所述磁通量目标信号（320）代表所述伺服阀（220）中的期望磁通量测量结果，并且从所述多个磁通量目标信号（320）中生成多个磁通量差信号（325）哪个代表 t期望磁通量测量和当前磁通量测量之间的差异，以及使用多个磁通目标信号（320）来调节伺服阀（220）的组件。其他实施例可以被描述。

63. 发明公开

EP3225544A1 TOUCHDOWN ORIENTATION CONTROL SYSTEM FOR A ROTARY WING AIRCRAFT AND METHOD 失效
标题翻译：旋翼式飞机的触角定向控制系统及方法
公开(公告)号：EP3225544A1
公开(公告)日：2017-10-04
申请号：EP17153286.4
申请日：2017-01-26
申请人： Sikorsky Aircraft Corporation
发明人： LITWINOWICZ, Anthony
IPC分类号： B64C27/57 , B64C13/50 , G05D1/10
CPC分类号： G05D1/0676 , B64C13/503 , B64C27/04 , B64C27/57 , B64C27/82 , G05D1/0858
摘要： A rotary wing aircraft control system includes an airframe, a main rotor assembly supported by the airframe, and a control system arranged in the airframe and operatively connected to the main rotor assembly. The control system includes a flight control computer (FCC), at least one control inceptor device and a touchdown orientation control system. The touchdown orientation control system includes a computer readable program code an FCC to: sense, by a sensor operatively connected to the flight control computer (FCC), an altitude of the rotary wing aircraft relative to a landing surface, determine one of a landing state rearward velocity reference limit value and a landing state lateral velocity reference limit value associated with the altitude, and selectively limit a landing state flight envelope of the rotary wing aircraft to the one of the landing state rearward velocity reference limit value and the landing state lateral velocity reference limit value.
摘要翻译：旋翼飞行器控制系统包括机身，由机身支撑的主旋翼组件以及布置在机身中并可操作地连接至主旋翼组件的控制系统。该控制系统包括飞行控制计算机（FCC），至少一个控制感应器装置和触地定向控制系统。触地定向控制系统包括计算机可读程序代码FCC，以便：通过可操作地连接到飞行控制计算机（FCC）的传感器感测旋翼飞机相对于着陆表面的高度，确定着陆状态后方速度基准极限值和与该高度相关联的着陆状态横向速度基准极限值，并且选择性地将旋翼飞行器的着陆状态飞行包络限制到着陆状态后退速度基准极限值和着陆状态横向速度参考极限值。

64. 发明公开

EP3225540A1 FORCE FIGHT MITIGATION 有权转让
标题翻译：强制战斗缓解
公开(公告)号：EP3225540A1
公开(公告)日：2017-10-04
申请号：EP16305368.9
申请日：2016-03-30
申请人： Goodrich Actuation Systems SAS
发明人： JUDEY, Jeremy
IPC分类号： B64C13/42 , B64C13/50
摘要： A force fight mitigation system comprising: control means configured to provide a position command to each of two or more actuators arranged to position a surface, the position command indicative of a desired position of the actuator relative to the surface; means to detect the actual position of the actuator relative to the surface in response to the position command; and means to determine an offset between the desired position and the actual position and to store a rigging correction based on the offset; wherein, for each actuator, an offset is determined for each of three or more desired positions.
摘要翻译：一种力控制减轻系统，包括：控制装置，被配置为向布置成定位表面的两个或更多致动器中的每一个提供位置命令，所述位置命令指示所述致动器相对于所述表面的期望位置; 响应于位置命令检测致动器相对于表面的实际位置的装置; 以及用于确定期望位置与实际位置之间的偏移并基于该偏移存储索具校正的装置; 其中，对于每个致动器，针对三个或更多个期望位置中的每一个确定偏移。

65. 发明授权

EP2955104B1 System and method for moving a high lift surface relative to the wing of an aircraft 有权
标题翻译：用于相对于飞机机翼移动高升力表面的系统和方法
公开(公告)号：EP2955104B1
公开(公告)日：2017-08-09
申请号：EP14171960.9
申请日：2014-06-11
申请人： Airbus Operations GmbH
发明人： Dege, Saskia
IPC分类号： B64C9/02 , B64C13/28 , B64C13/42 , B64C13/50 , B64D45/00 , B64C3/50
CPC分类号： B64C13/28 , B64C9/02 , B64C13/42 , B64D2045/001

66. 发明授权

EP2097315B1 CONTROL STICK ADAPTED FOR USE IN A FLY-BY-WIRE FLIGHT CONTROL SYSTEM, AND LINKAGE FOR USE THEREIN 失效
标题翻译：控制棒适用于飞行电子飞行控制系统及其使用的连接
公开(公告)号：EP2097315B1
公开(公告)日：2017-07-26
申请号：EP07836604.4
申请日：2007-08-08
申请人： Moog Inc.
发明人： KOPP, John, D.
IPC分类号： B64C13/04 , B64C13/12 , B64C13/50
CPC分类号： B64C13/04 , F16F1/14 , G05G2009/04718 , G05G2009/04766 , Y10T74/20201

67. 发明授权

EP2170700B2 FLY-BY-WIRE FLIGHT CONTROL SYSTEM WITH ELECTRONIC LEAD/LAG DAMPER ALGORITHM 有权
标题翻译： FLY-BY-WIRE-FLUGSTEUERUNGSSYSTEM MIT ELEKTRONISCHEM LEAD / LAG-DÄMPFER-ALGORITHMUS
公开(公告)号：EP2170700B2
公开(公告)日：2017-05-03
申请号：EP08829369
申请日：2008-06-19
申请人： SIKORSKY AIRCRAFT CORP
发明人： SAHASRABUDHE VINEET , GOLD PHILLIP J
IPC分类号： B64C27/51 , B64C13/50 , B64C27/04 , B64C27/35 , G05D1/08
CPC分类号： B64C13/503 , G05D1/0858

68. 发明公开

EP2518578A3 Flight controller management system with a backdrive monitor 有权
标题翻译：空中交通管制员的管理制度与Rotovariatormonitor
公开(公告)号：EP2518578A3
公开(公告)日：2017-04-12
申请号：EP12165568.2
申请日：2012-04-25
申请人： The Boeing Company
发明人： Krogh, Steven Barry , Bresley, William Milo , Conner, Ian M. , Levine, Benjamin D , Minteer-Levine, Jasmine Beth , Pettit, Ryan L.
IPC分类号： G05D1/00 , B64C13/10 , B64C13/18 , B64D45/00 , B64C13/50
CPC分类号： G05D1/0061 , B64C13/10 , B64C13/18 , B64C13/503 , B64D45/0005
摘要： A method and apparatus for a monitoring module. The monitoring module is configured to identify a difference between measured position information for a controller and expected position information for the controller. The monitoring module is configured to compare the difference with thresholds for managing an autopilot in a control system of a vehicle to form a comparison. The monitoring module is configured to manage an operation of the autopilot based on the comparison such that the autopilot remains operating when a backdrive system is inoperative and an intentional override of the autopilot is absent.

69. 发明公开

EP3145810A1 ACTIONNEUR DE COMMANDE D'UNE GOUVERNE DE VOL 有权
标题翻译： AKTUATOR ZUR STEUERUNG EINERFLUGSTEUERFLÄCHE
公开(公告)号：EP3145810A1
公开(公告)日：2017-03-29
申请号：EP15725569.6
申请日：2015-05-21
申请人： Safran Electronics & Defense
发明人： CHAVIGNIER, Louis , LEBRUN, Marc , VIENNOT, Severin
IPC分类号： B64C13/50 , B64C13/28 , F16H1/28 , F16H25/20
CPC分类号： B64C13/28 , F16H1/28 , F16H25/2015 , F16H25/205 , F16H25/2454
摘要： The invention relates to an actuator (4) for controlling a flight control surface (3) of an aircraft, comprising: - a primary route (5) comprising a first member (8) for generating a first torque, and a first drive shaft (10) having an end (18) able to be connected to the first member (8) and an end (19) able to be connected to the control surface (3), - a secondary route (6) comprising a second member (24) for generating a second torque and a second drive shaft (26) having an end (45) able to be connected to the second member (24) and an end (46) able to be connected to the control surface (3), in which actuator the second drive shaft (10) is hollow and extends around the first drive shaft (26).
摘要翻译：本发明涉及一种用于控制飞机的飞行控制表面（3）的致动器（4），包括：主要路线（5），包括用于产生第一扭矩的第一构件（8）和第一驱动轴具有能够连接到第一构件（8）的端部（18）和能够连接到控制表面（3）的端部（19）的第二路径（6），包括第二构件（24））和具有能够连接到第二构件（24）的端部（45）的第二驱动轴（26）和能够连接到控制表面（3）的端部（46），在第二驱动轴所述致动器第二驱动轴（10）是中空的并围绕第一驱动轴（26）延伸。

70. 发明授权

EP2492770B1 Electronic device integrity monitoring apparatus 有权
标题翻译：设备用于监控电子设备的完整性
公开(公告)号：EP2492770B1
公开(公告)日：2017-01-04
申请号：EP12155006.5
申请日：2012-02-10
申请人： Nabtesco Corporation
发明人： NAKAGAWA, Shingo
IPC分类号： G05B23/02 , B64C13/50 , B64D45/00
CPC分类号： G05B23/0237 , B64C13/50 , B64D2045/0085

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