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1. 发明公开

EP3371048A1 PROGRAMMABLE MOTOR CONTROLLER USING A MOTOR 有权
公开(公告)号：EP3371048A1
公开(公告)日：2018-09-12
申请号：EP16908458.9
申请日：2016-07-14
申请人： SZ DJI Technology Co., Ltd.
发明人： LIU, Wanqi , LAN, Qiu , ZHOU, Changxing
IPC分类号： B64C27/12 , B64C13/04 , B64C27/56
CPC分类号： B64C13/04 , B64C27/12 , B64C27/56 , B64C2201/042 , B64C2201/141 , B64D31/06 , H02P6/182 , H02P21/0025 , H02P23/0031 , H02P27/08
摘要： A method for operating a motor controller includes obtaining an electrical signal via a port on the motor controller and selecting a motor control parameter from a plurality of different motor control parameters based on the electrical signal. The port is configured to be electrically connected to a motor. The motor controller is configured to control the motor based on the selected motor control parameter.

2. 发明公开

EP3224136A1 SYSTEM AND METHOD TO INTERCHANGE FLIGHT CONTROL INCEPTORS IN AN AIRCRAFT FLIGHT CONTROL SYSTEM AND COCKPIT 有权转让
标题翻译：在飞机飞行控制系统和驾驶舱中交换飞行控制感受器的系统和方法
公开(公告)号：EP3224136A1
公开(公告)日：2017-10-04
申请号：EP15808319.6
申请日：2015-11-25
申请人： Embraer S.A.
发明人： DE MIRANDA CARÁ, Guilherme , CHAVES, Nilson Emanuel Bezerra , FONSECA, Celso Jose Amaral , CAMPOS, Marcos Vinícius
IPC分类号： B64C13/04 , B64C27/56
CPC分类号： B64C13/04 , B64C13/06 , B64C27/56 , B64D11/0689 , Y02T50/44
摘要： A flexible flight control system enables conversion from one architecture using one type of inceptor to another architecture using another type of inceptor, through the usage of modular software and hardware pieces with common interfaces among the different types of inceptors. Longitudinal and lateral directional control laws are adapted to be compatible with the specific aspects of the operation of each configuration/architecture, giving the option to the aircraft operator to choose any one of a number of inceptor architectures at time of manufacture.
摘要翻译：灵活的飞行控制系统通过使用不同类型的感受器之间具有共同接口的模块化软件和硬件片段，能够使用一种类型的感受器从一种架构转换为另一种类型的感受器的架构。纵向和横向方向控制法则适合于与每个配置/架构的操作的特定方面相兼容，给予航空器运营商在制造时选择多种感应器架构中的任何一种的选项。

3. 发明授权

EP2952431B1 DISPOSITIF D ALERTE D'UN PILOTE DE GIRAVION PAR SIGNAUX TACTILES, METTANT EN OEUVRE UN « VÉRIN DE TRIM » RELIÉ À UN ORGANE DE COMMANDE DE VOL 有权
标题翻译：警告摇摆飞机搭载BY触觉信号的掌舵系统将在连纵倾液压缸使用的飞行控制装置ONE IS COMING
公开(公告)号：EP2952431B1
公开(公告)日：2016-07-27
申请号：EP15168476.8
申请日：2015-05-20
申请人： Airbus Helicopters
发明人： Sandri, Florence
IPC分类号： B64C27/56 , B64C13/10 , B64C13/46
CPC分类号： B64C13/10 , B64C13/18 , B64C13/46 , B64C27/56 , G08B6/00

4. 发明授权

EP2415669B1 Control system 有权转让
公开(公告)号：EP2415669B1
公开(公告)日：2015-05-13
申请号：EP10400037.7
申请日：2010-08-04
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH
发明人： Boris Grohmann , Gregor Paulmann
IPC分类号： B64C27/56 , B64C13/42
CPC分类号： B64C13/42 , B64C27/56

5. 发明公开

EP2812764A2 AUTOPILOT AND METHODS 有权
标题翻译： AUTOPILOT UND VERFAHREN
公开(公告)号：EP2812764A2
公开(公告)日：2014-12-17
申请号：EP13787117.4
申请日：2013-02-08
申请人： Merlin Technology Inc.
发明人： ALBION, Nicolas , BARTEL, Mark , FEIFEL, Marc , MARVIN, Mark , MERCER, John
IPC分类号： G05D1/00 , B64C27/04 , B64C13/18
CPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/0077 , G05D1/0816 , G05D1/0858 , G05D1/102 , Y02T50/44
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.
摘要翻译：直升机自动驾驶系统包括用于直升机飞行的姿态保持的内循环，包括施加到内循环的给定水平的冗余。外部环路被配置为提供关于直升机的飞行的导航功能，其包括与内部循环不同的冗余级别。致动器在联动装置上提供制动力，用于在停电期间稳定直升机的飞行。致动器是机电的并且接收电驱动信号以提供直升机的自动飞行控制，而不需要直升机中的液压辅助系统。自动驾驶仪可以在液压辅助系统的故障模式下操作直升机。使用相关的传感器输入描述多个飞行模式，包括基于速率和真实姿态模式。

6. 发明授权

EP2626296B1 Pilot control system with compact gimbal mechanism 有权
标题翻译：与紧凑型万向接头先导控制系统
公开(公告)号：EP2626296B1
公开(公告)日：2014-08-13
申请号：EP13153191.5
申请日：2013-01-30
申请人： Bell Helicopter Textron Inc.
发明人： Yates, Travis L , Linton, Bradley D
IPC分类号： B64C13/04 , B64C27/56
CPC分类号： F01D7/00 , B64C13/04 , B64C27/56 , B64D43/00 , G05G9/047 , G05G2009/04703

7. 发明授权

EP2626301B1 Pilot control system with pendent grip 有权
标题翻译：与杠杆手柄先导控制系统
公开(公告)号：EP2626301B1
公开(公告)日：2014-07-16
申请号：EP13153192.3
申请日：2013-01-30
申请人： Bell Helicopter Textron Inc.
发明人： Yates, Travis L , Linton, Bradley D , Haugeberg, Chad R
IPC分类号： B64C27/56 , B64C13/04
CPC分类号： B64C13/04 , B64C27/56

8. 发明公开

EP2626300A1 Pilot control system with hand rest 有权
标题翻译： Handstütze
公开(公告)号：EP2626300A1
公开(公告)日：2013-08-14
申请号：EP13153189.9
申请日：2013-01-30
申请人： Bell Helicopter Textron Inc.
发明人： Yates, Travis L , Linton, Bradley D
IPC分类号： B64C27/56 , B64C13/04
CPC分类号： B64C27/56 , B64C13/04 , Y10T74/20612
摘要： According to one embodiment, a control assembly (200) includes a post (210), a grip (230), and a hand rest (240). The post has a top, a bottom, and a body joining the top to the bottom. The grip (230) is positioned at least partially above the post (210) and is movable along at least one arc (232). The hand rest (240) is coupled to the top and comprises an upper surface having a profile (242) corresponding to the at least one arc.
摘要翻译：根据一个实施例，控制组件（200）包括柱（210），手柄（230）和扶手（240）。该柱具有顶部，底部和与顶部连接的底部。手柄（230）至少部分地定位在柱（210）的上方，并且可沿着至少一个弧（232）移动。扶手（240）联接到顶部并且包括具有对应于至少一个弧的轮廓（242）的上表面。

9. 发明公开

EP2626296A1 Pilot control system with compact gimbal mechanism 有权
标题翻译： Plotensteuerungsystem mit kompaktem Kardanmechanismus
公开(公告)号：EP2626296A1
公开(公告)日：2013-08-14
申请号：EP13153191.5
申请日：2013-01-30
申请人： Bell Helicopter Textron Inc.
发明人： Yates, Travis L , Linton, Bradley D
IPC分类号： B64C13/04 , B64C27/56
CPC分类号： F01D7/00 , B64C13/04 , B64C27/56 , B64D43/00 , G05G9/047 , G05G2009/04703
摘要： According to one embodiment, a control assembly (200) includes a first gimbal (260) and a second gimbal (270). The first gimbal (260) is rotatable about a first axis of rotation. The first gimbal (260) comprises a first linkage attachment point offset from the first axis of rotation. The second gimbal (270) is rotatably coupled to the first gimbal (260) and rotatable relative to the first gimbal (260) about a second axis of rotation. The second gimbal (270) comprises a second linkage attachment point offset from the second axis of rotation and a control shaft attachment point.
摘要翻译：根据一个实施例，控制组件（200）包括第一万向架（260）和第二万向架（270）。第一万向架（260）可围绕第一旋转轴线旋转。第一万向架（260）包括从第一旋转轴线偏移的第一连杆附接点。第二万向架（270）可旋转地联接到第一万向架（260）并且可围绕第二旋转轴线相对于第一万向架（260）旋转。第二万向节（270）包括从第二旋转轴线偏移的第二连杆附接点和控制轴附接点。

10. 发明授权

EP1704345B1 ROTARY WING AIRCRAFT ROD END AND METHOD OF MAKING A HELICOPTER VEHICLE ROD END WITH A PRECOCKED ORIENTATION 失效
标题翻译：挥杆平面杆端并产生一个直升机杆头具有预倾斜取向方法
公开(公告)号：EP1704345B1
公开(公告)日：2012-03-07
申请号：EP05726379.0
申请日：2005-01-14
申请人： LORD CORPORATION
发明人： JAMES, Frank, O. , RAJECKI, Christopher, F.
IPC分类号： F16F1/393 , B64C27/56 , B64C27/59
CPC分类号： F16F1/40 , B64C27/56 , B64C27/58 , B64C27/59 , F16C7/04 , F16C11/0614 , F16C11/083 , F16F1/393 , Y10T29/49885 , Y10T29/4998 , Y10T29/49982 , Y10T403/47
摘要： The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

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