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1. 发明授权

US11926407B2 Jam tolerant rotary actuator 有权
公开(公告)号：US11926407B2
公开(公告)日：2024-03-12
申请号：US17737729
申请日：2022-05-05
申请人： Eaton Intelligent Power Limited
发明人： Daniel Henry Roberts
IPC分类号： B64C13/34 , B64C13/28 , F16H57/02
CPC分类号： B64C13/341 , B64C13/34 , F16H57/02
摘要： Various flight control components can be operated through gearbox driven rotary actuators. In the event of a jam occurring the gearbox, the gearbox can be decoupled from a surrounding support housing to enable free-trailing or limited motion relative to the support housing. The motion may or may not be damped. Decoupling the gearbox enables the flight control component to move to a neutral or non-interfering position even when user control over the component has been lost.

2. 发明授权

US10000276B2 Pushing device, moving mechanism and aircraft 有权
公开(公告)号：US10000276B2
公开(公告)日：2018-06-19
申请号：US15134711
申请日：2016-04-21
申请人： AIRBUS (BEIJING) ENGINEERING CENTRE COMPANY LIMITED
发明人： Ming Li , Yumin Sun
IPC分类号： B64C13/28 , B64C9/16 , B64C13/00 , B64C13/42 , B64C9/14 , F03G1/10
CPC分类号： B64C13/341 , B64C9/14 , B64C9/16 , B64C13/00 , B64C2009/143 , F03G1/10
摘要： The present application relates to a pushing device, a moving mechanism and an aircraft. According to an aspect of the present application, a pushing device for a moving mechanism of an aircraft is provided, the moving mechanism including a primary moving device and an auxiliary moving device assisting the primary moving device, the pushing device including a support member and a pushing assembly supported by the support member, and the pushing assembly including a pushing element and an energy storage element. The pushing element is adapted to push a broken part of the auxiliary moving device to an offset position from a normal working position by means of energy from the energy storage element when the auxiliary moving device breaks. According to the present application, it is possible to provide an effective fault protection to the moving mechanism of the aircraft.

3. 发明授权

US09870004B2 High authority stability and control augmentation system 有权
公开(公告)号：US09870004B2
公开(公告)日：2018-01-16
申请号：US14284045
申请日：2014-05-21
申请人： Bell Helicopter Textron Inc.
发明人： Brady G. Atkins , James E. Harris , Carl D. Griffith
IPC分类号： G01C23/00 , G05D1/08 , G05D1/00
CPC分类号： G05D1/0833 , B64C13/341 , B64C27/58 , G05D1/0077 , B64C2027/7283 , B64C27/001
摘要： A method of increasing the control authority of redundant stability and control augmentation system (SCAS) actuators by utilizing feedback between systems such that one system may compensate for the position of a failed actuator of the other system. Each system uses an appropriate combination of reliable and unreliable inputs such that unreliable inputs cannot inappropriately utilize the increased authority. Each system may reconfigure itself when the other system actuator fails at certain positions so that the pilot or other upstream input maintains sufficient control authority of the aircraft.

4. 发明申请

US20140027565A1 ROTORCRAFT ADVANCED AUTOPILOT CONTROL ARRANGEMENT AND METHODS 审中-公开
标题翻译：旋转高级自动控制装置和方法
公开(公告)号：US20140027565A1
公开(公告)日：2014-01-30
申请号：US13763582
申请日：2013-02-08
申请人： Merlin Technology, Inc.
发明人： Mark Marvin , Marc Feifel , Nicolas Albion , John E. Mercer
IPC分类号： B64C27/57
CPC分类号： B64C27/57 , B64C13/0421 , B64C13/044 , B64C13/341 , B64C27/58 , G05D1/0858
摘要： An autopilot system includes an actuator arrangement that receives control signals to influence the flight of the helicopter in a selected one of a plurality of different flight modes. A control stick input arrangement allows flight mode selection and control with no more than a particular one of the pilot's hands in the engaged position on the stick and without moving the hand away from the engaged position. A slaved gyro output signal is based on no more than the set of sensor outputs used by the autopilot such that an autopilot display presents autopilot flight mode information while displaying a slaved gyro output. The autopilot provides for pilot selection of one of a subset of the plurality of flight modes which is customized based on a current flight status of the helicopter. An automatic autorotation mode is provided.
摘要翻译：自动驾驶仪系统包括致动器装置，该致动器装置接收控制信号以影响直升机在多种不同飞行模式中所选择的一种中的飞行。控制杆输入装置允许飞行模式的选择和控制，不超过驾驶员手中特定的一只手在杆上的接合位置，而不用将手从接合位置移开。从动陀螺仪输出信号基于自动驾驶仪使用的传感器输出集合，使得自动驾驶仪显示器显示自动驾驶飞行模式信息，同时显示从属陀螺仪输出。自动驾驶仪提供了基于直升机的当前飞行状态来定制的多个飞行模式的子集中的一个的飞行员选择。提供自动自动转换模式。

5. 发明申请

US20120181383A1 HYDRAULIC ACTUATOR SYSTEM 审中-公开
标题翻译：液压执行器系统
公开(公告)号：US20120181383A1
公开(公告)日：2012-07-19
申请号：US13349017
申请日：2012-01-12
申请人： Kazuyuki Suzuki , Koji Itoh
发明人： Kazuyuki Suzuki , Koji Itoh
IPC分类号： B64C13/36
CPC分类号： B64C9/02 , B64C13/341 , B64C13/505
摘要： A hydraulic actuator system 1 is provided for driving a movable portion attached to a wing 5 of an airplane. A plurality of first system hydraulic actuators 2 and a plurality of second system hydraulic actuators 3 are included and are connected to the movable portion. The first system hydraulic actuators 2 are attached to the wing 5 and connected to a first hydraulic pressure source, whereas the second system hydraulic actuators 3 are attached to the wing to be in parallel to the first system hydraulic actuators 2 and are connected to a second hydraulic pressure source. The first system hydraulic actuators 2 and the second system hydraulic actuators 3 are alternately provided at a predetermined part of the wing 5.
摘要翻译：液压致动器系统1被设置用于驱动附接到飞机的机翼5的可移动部分。包括多个第一系统液压致动器2和多个第二系统液压致动器3并连接到可动部分。第一系统液压致动器2附接到翼5并连接到第一液压源，而第二系统液压致动器3附接到机翼以与第一系统液压致动器2平行并且连接到第二液压致动器2 液压源。第一系统液压致动器2和第二系统液压致动器3交替地设置在机翼5的预定部分。

6. 发明申请

US20090206197A1 Actuator and flap arrangement with actuator interconnection 审中-公开
标题翻译：执行器和活门排列与执行器互连
公开(公告)号：US20090206197A1
公开(公告)日：2009-08-20
申请号：US11440558
申请日：2006-05-25
申请人： Arthur Degenholtz , Edward Mayer , Naresh P. Vaghela
发明人： Arthur Degenholtz , Edward Mayer , Naresh P. Vaghela
IPC分类号： B64C9/00
CPC分类号： B64C13/24 , B64C13/341 , B64C13/505 , B64D45/0005 , B64D2045/001 , Y02T50/44
摘要： An actuator and flap arrangement includes a flap, movable relative to a support structure, and two actuators. Each actuator has a portion fixed relative to the support structure, a portion movable relative to the fixed portion and connected to the flap for transfer of motor force to flap upon movement of the movable portion, and a motor for moving the movable portion relative to the fixed portion. The arrangement also includes a device interconnecting the two actuators for transferring motive force between the two actuators.
摘要翻译：致动器和翼片装置包括可相对于支撑结构移动的翼片和两个致动器。每个致动器具有相对于支撑结构固定的部分，一部分相对于固定部分可移动并连接到翼片，用于在可移动部分移动时将马达的力传递到翼片;以及马达，用于使可动部分相对于固定部分。该装置还包括将两个致动器互连以在两个致动器之间传递动力的装置。

7. 发明授权

US10843796B2 Rotorcraft advanced autopilot control arrangement and methods 有权
公开(公告)号：US10843796B2
公开(公告)日：2020-11-24
申请号：US13763582
申请日：2013-02-08
申请人： Merlin Technology, Inc.
发明人： Mark Marvin , Marc Feifel , Nicholas Albion , John E. Mercer
IPC分类号： B64C27/57 , B64C13/28 , B64C13/04 , B64C27/58 , G05D1/08
CPC分类号： B64C27/57 , B64C13/0421 , B64C13/341 , B64C27/58 , G05D1/0858 , B64C13/044
摘要： An autopilot system includes an actuator arrangement that receives control signals to influence the flight of the helicopter in a selected one of a plurality of different flight modes. A control stick input arrangement allows flight mode selection and control with no more than a particular one of the pilot's hands in the engaged position on the stick and without moving the hand away from the engaged position. A slaved gyro output signal is based on no more than the set of sensor outputs used by the autopilot such that an autopilot display presents autopilot flight mode information while displaying a slaved gyro output. The autopilot provides for pilot selection of one of a subset of the plurality of flight modes which is customized based on a current flight status of the helicopter. An automatic autorotation mode is provided.

8. 发明申请

US20180157275A1 High Authority Stability and Control Augmentation System 审中-公开
公开(公告)号：US20180157275A1
公开(公告)日：2018-06-07
申请号：US15872651
申请日：2018-01-16
申请人： Bell Helicopter Textron Inc.
发明人： Brady G. Atkins , James E. Harris , Carl D. Griffith
IPC分类号： G05D1/08 , G05D1/00
CPC分类号： G05D1/0833 , B64C13/341 , B64C27/58 , G05D1/0077 , B64C2027/7283 , B64C27/001
摘要： A system and method of increasing the control authority of redundant stability and control augmentation system (SCAS) actuators by utilizing feedback between systems such that one system may compensate for the position of a failed actuator of the other system. Each system uses an appropriate combination of reliable and unreliable inputs such that unreliable inputs cannot inappropriately utilize the increased authority. Each system may reconfigure itself when the other system actuator fails at certain positions so that the pilot or other upstream input maintains sufficient control authority of the aircraft.

9. 发明申请

US20180141643A1 GEARBOX ASSEMBLY 审中-公开
公开(公告)号：US20180141643A1
公开(公告)日：2018-05-24
申请号：US15710861
申请日：2017-09-21
申请人： Ratier-Figeac SAS
发明人： Christian Fages
IPC分类号： B64C13/34 , B64C13/10 , F16H1/20 , F16H55/08
CPC分类号： B64C13/34 , B64C13/10 , B64C13/341 , B64C19/00 , F16D9/06 , F16D2250/0061 , F16H1/206 , F16H35/10 , F16H55/0846
摘要： A transmission or gearbox assembly with fail-safe means for providing redundancy where failure can lead to loss of torque transmission between component parts of the assembly, the assembly comprising a plurality of first components in torque transmitting engagement and at least one second component associated with at least one of the first components, the second component being joined to the respective first component by a discontinuous joint. Preferably, each first component of the system has a corresponding second component joined thereto by a discontinuous joint.

10. 发明申请

US20180072403A1 FAILSAFE BAR CONNECTION 审中-公开
公开(公告)号：US20180072403A1
公开(公告)日：2018-03-15
申请号：US15698770
申请日：2017-09-08
申请人： Ratier-Figeac SAS
发明人： Frédéric Vermande
IPC分类号： B64C13/42 , F16H25/20
CPC分类号： F16H25/205 , B64C13/28 , B64C13/341 , F16H25/2015 , F16H25/2021 , F16H2025/2037 , F16H2057/018
摘要： A failsafe bar connection of a screw actuator includes a failsafe bar for transmitting load via a secondary load path, the failsafe bar having a bar-end with a convex thrust surface; and an attachment part for coupling load to an aircraft structure, the attachment part having a socket for retention of the bar-end, the socket providing a concave thrust surface. A contact mechanism is provided to monitor relative displacement of the convex thrust surface within the concave thrust surface in a direction along an axis of the attachment part. In this way, changes in backlash and loading of the secondary load path can be detected. The contact mechanism comprises a protuberance extending from the bar-end along the main rotational axis of the failsafe bar and a displaceable contact surface provided by a displaceable member in the attachment part, the relative position of which is monitored by a displacement sensor.

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