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1. 发明申请

US20190210712A1 FLIGHT CONTROL SURFACE ASSEMBLY 审中-公开
公开(公告)号：US20190210712A1
公开(公告)日：2019-07-11
申请号：US16230146
申请日：2018-12-21
申请人： Airbus Operations GmbH
发明人： Bernhard Schlipf , Peter Lücken
IPC分类号： B64C13/50 , B64C3/38 , B64C9/26 , B64C9/20 , B64C9/02
CPC分类号： B64C13/50 , B64C3/38 , B64C9/02 , B64C9/20 , B64C9/26 , B64C13/503 , B64D45/0005 , B64D2045/001
摘要： A flight control surface assembly for mounting to a main wing of an aircraft includes flight control surfaces side by side with a gap between each two of them, a connection assembly for movably connecting the flight control surfaces to the main wing to be selectively movable in a predetermined synchronous movement between retracted and extended positions, a drive arrangement operable to effect predetermined synchronous movement, and a control unit connected to the drive arrangement to control the drive arrangement. The flight control surface assembly includes for each gap a separate pair of electrical components with a first electrical component and a second electrical component fixedly mounted to a another one of the two flight control surfaces separated by the gap. The first and second electrical components of each pair are configured to wirelessly transfer electrical energy over the gap.

2. 发明申请

US20180281987A1 METHODS AND APPARATUS FOR DETECTING AIRFLOW CONTROL SURFACE SKEW CONDITIONS 审中-公开
公开(公告)号：US20180281987A1
公开(公告)日：2018-10-04
申请号：US15474261
申请日：2017-03-30
申请人： The Boeing Company
发明人： Harvey C. Nelson , Christopher E. Plass
IPC分类号： B64D45/00 , G08B21/18
CPC分类号： B64D45/0005 , B64C9/16 , B64C13/28 , B64D2045/001 , G08B21/187
摘要： Methods and apparatus for detecting airflow control surface skew conditions are disclosed herein. An example apparatus includes an aircraft wing, a support linkage, and a flap coupled to the aircraft wing via the support linkage. The example apparatus includes a sensor coupled to the flap at a location proximate to the support linkage. The sensor is configured to generate vibration data for the location. The example apparatus includes a detector communicatively coupled to the sensor. The detector is to detect a skew condition of the flap based on the vibration data.

3. 发明申请

US20170355449A1 ELECTRICAL ARCHITECTURE FOR SLAT/FLAP CONTROL USING SMART SENSORS AND EFFECTORS 审中-公开
公开(公告)号：US20170355449A1
公开(公告)日：2017-12-14
申请号：US15293510
申请日：2016-10-14
申请人： Goodrich Aerospace Services Private Limited
发明人： Shardul Shrinivas Bapat , Shihab T.A. Muhammed , Pradeep Chitirala
IPC分类号： B64C13/50 , B64D45/00 , B64C9/22 , B64C13/04 , H04L12/403 , H04L12/40
CPC分类号： B64C13/503 , B64C9/22 , B64C13/04 , B64C13/0425 , B64D45/0005 , B64D2045/001 , B64D2221/00 , G05D1/0077 , H04L12/403 , H04L2012/40215 , H04L2012/4028 , Y02T50/44
摘要： A centralized control system and/or method for controlling an aircraft are provided. The centralized control system includes a controller configured to receive a device signal and transmit a control signal, a communication bus connected to the controller being configured to transport the device signal and the control signal, a plurality of devices connected to the controller using the communication bus, wherein at least one of the plurality of devices includes at least one of a sensor being configured to collect the device signal and an effector configured to respond to the control signal, and a bus communication circuit configured to communicate over the communication bus to the controller.

4. 发明授权

US09821902B2 High lift control method and system for aircraft 有权
公开(公告)号：US09821902B2
公开(公告)日：2017-11-21
申请号：US14771974
申请日：2014-02-26
申请人： Bombardier Inc.
发明人： Robert Young , Yves Grenier , Hany Sadek
IPC分类号： B64C13/04 , B64C13/16 , B64C9/28 , B64D45/00
CPC分类号： B64C13/04 , B64C9/28 , B64C13/16 , B64D2045/001
摘要： A high lift control system for an aircraft having at least one high lift surface includes a selector having a predetermined number of discrete positions, at least one of the predetermined positions corresponding to different positions of the at least one high lift surface.

5. 发明授权

US09701421B2 Method for determining the position of a component in a high lift system of an aircraft, high lift system of an aircraft and aircraft 有权
公开(公告)号：US09701421B2
公开(公告)日：2017-07-11
申请号：US14720013
申请日：2015-05-22
申请人： Airbus Operations GmbH
发明人： Eugen Neb , Jörg Wyrembek , Vincent Maire
IPC分类号： B64D45/00 , B64C9/00 , B64C13/16 , B64C9/16 , B64C9/22 , B64C13/18 , B64C13/28
CPC分类号： B64D45/0005 , B64C9/00 , B64C9/16 , B64C9/22 , B64C13/16 , B64C13/28 , B64D2045/001
摘要： A method for determining the position of a component in a high lift system of an aircraft, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and actuator drive stations coupled with the power control unit and movable high lift surfaces. The method comprises the steps of acquiring a first rotational position of a first position pick-off unit mechanically coupled with the power control unit by means of a first gear having a first gear ratio, acquiring at least one second rotational position of at least one second position pick-off unit mechanically coupled with a driven element in at least one drive station, and determining the number of full rotations the first position pick-off unit has already accomplished between a neutral position and an intended maximum number of rotations.

6. 发明授权

US09688418B2 Method for determining a state of a component in a high lift system of an aircraft, high lift system of an aircraft, and aircraft having such a high lift system 有权
公开(公告)号：US09688418B2
公开(公告)日：2017-06-27
申请号：US14920428
申请日：2015-10-22
申请人： Airbus Operations GmbH
发明人： Eugen Neb , Jan-Arend Van Bruggen , Michael Brady , Joerg Wyrembek , Olivier Criou , Jan Haserodt , Mark Heintjes
IPC分类号： G01M17/00 , B64D45/00 , B64C9/20 , B64C13/16 , B64C9/16
CPC分类号： B64D45/0005 , B64C9/20 , B64C13/16 , B64D2045/001
摘要： A method for determining a state of a component in a high lift system of an aircraft is proposed, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces.

7. 发明授权

US09638592B2 Differential motion sensor 有权
公开(公告)号：US09638592B2
公开(公告)日：2017-05-02
申请号：US14510594
申请日：2014-10-09
申请人： Hamilton Sundstrand Corporation
发明人： Stephen Davies , Michael Carbone
IPC分类号： G01L5/00 , B64D45/00 , G01B5/00 , G01B5/14
CPC分类号： G01L5/00 , B64D45/0005 , B64D2045/001 , G01B5/0025 , G01B5/14
摘要： A differential motion sensor includes a base and a cradle. The base includes a first surface that extends along a first axis to define a length and a second axis to define a width. The base further includes at least one hinge that pivots about a rotational axis extending along the first axis. The cradle is pivotably coupled to the at least one hinge and is configured to move in the direction of the second axis when pivoting about the hinge. The differential motion sensor is configured to operate in a first mode when the cradle is aligned with the base and a second mode when the cradle is pivotably displaced with respect to the base.

8. 发明申请

US20170038225A1 DIFFERENTIAL MOTION SENSOR 有权
标题翻译：差分运动传感器
公开(公告)号：US20170038225A1
公开(公告)日：2017-02-09
申请号：US14819943
申请日：2015-08-06
申请人： Hamilton Sundstrand Corporation
发明人： Michael Carbone , Scott C. Bonnett
IPC分类号： G01D5/12
CPC分类号： G01D5/12 , B64D45/0005 , B64D2045/001 , H01H35/006
摘要： An electromechanical differential motion sensor is disposed to detect transverse motion of a first piece relative to a second piece. The sensor includes a base anchored to the first piece, a lever arm that engages the second piece, a hinge, a retention mechanism, and a fuse wire. The hinge connects the lever arm to the base, such that the lever arm rotates relative to the base when the second piece displaces laterally with respect to the first piece. The retention mechanism retains the electromechanical differential motion sensor in a closed position wherein a first jaw of the base is aligned with a second jaw of the lever arm. The fuse wire carries an electrical signal current, and extends through the jaws such that transverse motion of the second piece relative to the first piece deflects the sensor from the closed position to an open position, thereby severing the first fuse wire.
摘要翻译：设置机电差速运动传感器以检测第一件相对于第二件的横向运动。传感器包括固定在第一部件上的基座，与第二部件接合的杠杆臂，铰链，保持机构和熔丝。铰链将杠杆臂连接到基座，使得当第二部件相对于第一部件横向移位时，杠杆臂相对于基座旋转。保持机构将机电差速运动传感器保持在关闭位置，其中基座的第一钳口与杠杆臂的第二钳口对准。保险丝线承载电信号电流，并延伸穿过钳口，使得第二件相对于第一件的横向运动将传感器从关闭位置偏转到打开位置，从而切断第一保险丝。

9. 发明申请

US20160337035A1 METHODS AND APPARATUSES INVOLVING FLEXIBLE CABLE/GUIDEWIRE/INTERCONNECTS 审中-公开
公开(公告)号：US20160337035A1
公开(公告)日：2016-11-17
申请号：US14949900
申请日：2015-11-24
申请人： John L. Erb
发明人： John L. Erb
IPC分类号： H04B10/25 , H04L29/08 , B64D45/00 , B63B45/00 , B60R16/023 , B60Q1/00
CPC分类号： H04B10/2504 , B60Q1/00 , B60R16/0231 , B63B45/00 , B64D45/00 , B64D45/0005 , B64D2045/001 , B64F1/14 , B64F1/20 , B64F1/205 , G02B6/4416 , G07C5/00 , H04B10/25 , H04B10/2503 , H04L12/28 , H04L49/15 , H04L67/12
摘要： Various embodiments of the present disclosure are directed toward apparatus and methods including communication circuits for communicating between a plurality of compartments in a vehicle. An array of flexible cables provides signal-communication paths between the plurality of compartments in the vehicle, with each cable having a glass or silica core region for conveying optical signals, and communicating signals (electrical signals and optical signals) along at least one of the signal-communication paths and between the plurality of compartments in the vehicle. The apparatus and methods also include a plurality of circuits that communicate status-indication signals between locations along the array of flexible cables. The status-indication signals are communicated via the signal-communication paths in the flexible array of cables and are indicative of vehicle-travel modes for reporting a status of the vehicle in a mode relative to travel of the vehicle.

10. 发明申请

US20160297541A1 AIRCRAFT WING SLAT SKEW DETECTION SYSTEMS AND METHODS 有权
标题翻译：飞机WING SLAT SKEW检测系统和方法
公开(公告)号：US20160297541A1
公开(公告)日：2016-10-13
申请号：US14683036
申请日：2015-04-09
申请人： The Boeing Company
发明人： Randall Eugene Anderson
IPC分类号： B64D45/00 , F16H19/04
CPC分类号： B64D45/0005 , B64D2045/001 , F16H19/04
摘要： An apparatus for detecting skew in a slat of an aircraft wing includes an elongated track moveably supported in the wing for longitudinal movement toward and away from a leading edge of the wing. The slat is coupled to a forward end of the track for conjoint movement therewith. An actuator is configured to selectably drive the track and slat between retracted and extended positions relative to the leading edge of the wing. A pinion gear is rotatably mounted in the wing and disposed in rolling engagement with a rack gear disposed on the track, and a sensor is coupled to the pinion gear and configured to sense the longitudinal position of the slat as a function of a rotational position of the pinion gear.
摘要翻译：一种用于检测飞机机翼的板条偏斜的装置包括可移动地支撑在机翼中的细长轨道，用于纵向移动并远离机翼的前缘。板条连接到轨道的前端，以与其一起运动。致动器构造成可选地驱动相对于机翼的前缘的缩回位置和延伸位置之间的轨道和缝翼。小齿轮可旋转地安装在机翼中并且与设置在轨道上的齿条滚动接合，并且传感器联接到小齿轮上，并且构造成根据旋转位置的函数来感测板条的纵向位置小齿轮。

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