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1. 发明授权

US07677868B2 Self-lubricated actuator for on-blade rotor control 有权
标题翻译：用于叶片转子控制的自润滑执行器
公开(公告)号：US07677868B2
公开(公告)日：2010-03-16
申请号：US11567773
申请日：2006-12-07
申请人： Zaffir Chaudhry , Andrew John Collins , Ulf J Jonsson , Fanping Sun , Brian E Wake , Michael G O'Callaghan , Jimmy Lin-Min Yeh
发明人： Zaffir Chaudhry , Andrew John Collins , Ulf J Jonsson , Fanping Sun , Brian E Wake , Michael G O'Callaghan , Jimmy Lin-Min Yeh
IPC分类号： F03B3/12
CPC分类号： B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： A self-lubricated actuator for a rotor blade flap of a helicopter having a housing; a motor having a shaft disposed in a bearing is provided. The actuator further has an output rod and a mechanism operatively associated with the motor and the output rod to transmit movement from the motor to the output rod. The housing includes a lubrication medium capable of substantially immersing the bearing, the motor shaft and the mechanism during operation.
摘要翻译：一种用于具有壳体的直升机的转子叶片翼片的自润滑致动器; 提供具有设置在轴承中的轴的马达。致动器还具有输出杆和与马达和输出杆可操作地相关联的机构，以将运动从马达传递到输出杆。壳体包括能够在运行期间基本上浸入轴承，马达轴和机构的润滑介质。

2. 发明申请

US20080138203A1 SELF-LUBRICATED ACTUATOR FOR ON-BLADE ROTOR CONTROL 有权
标题翻译：用于叶片转子控制的自润滑致动器
公开(公告)号：US20080138203A1
公开(公告)日：2008-06-12
申请号：US11567773
申请日：2006-12-07
申请人： Andrew John Collins , Zaffir Chaudhry , Ulf J Jonsson , Fanping Sun , Brian E. Wake , Michael G. O'Callaghan , Jimmy Lin-Min Yeh
发明人： Andrew John Collins , Zaffir Chaudhry , Ulf J Jonsson , Fanping Sun , Brian E. Wake , Michael G. O'Callaghan , Jimmy Lin-Min Yeh
IPC分类号： B64C27/615 , F01D25/18
CPC分类号： B64C27/615 , B64C2027/7266 , Y02T50/34
摘要： A self-lubricated actuator for a rotor blade flap of a helicopter having a housing; a motor having a shaft disposed in a bearing is provided. The actuator further has an output rod and a mechanism operatively associated with the motor and the output rod to transmit movement from the motor to the output rod. The housing includes a lubrication medium capable of substantially immersing the bearing, the motor shaft and the mechanism during operation.
摘要翻译：一种用于具有壳体的直升机的转子叶片翼片的自润滑致动器; 提供具有设置在轴承中的轴的马达。致动器还具有输出杆和与马达和输出杆可操作地相关联的机构，以将运动从马达传递到输出杆。壳体包括能够在运行期间基本上浸入轴承，马达轴和机构的润滑介质。

3. 发明申请

US20130186726A1 Electromagnetic Brake or Clutch and Method of Operation 审中-公开
标题翻译：电磁制动器或离合器及其操作方法
公开(公告)号：US20130186726A1
公开(公告)日：2013-07-25
申请号：US13814607
申请日：2011-08-12
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： F16D27/04
CPC分类号： F16D27/04 , F16D27/004 , F16D27/06 , F16D55/28 , F16D2055/0058 , F16D2121/22 , F16D2129/065 , H02K7/1025 , H02K7/106 , H02K7/1085 , H02K7/11
摘要： An electromagnetic brake or clutch includes a first face confronting a first face of a rotor disc, the discs being mounted for movement towards and away from the other; and a stator coil energized to urge the first face of the disc away from the first face of the rotor disc. In a first set of rotational positions, magnetic regions of one polarity on the first face of the brake or clutch disc confront magnetic regions of the opposite polarity on the first face of the rotor disc, and, in a second set of rotational positions of the shaft interposed between respective ones of the first set of rotational positions, magnetic regions of one polarity on the first face of the brake or clutch disc confront magnetic regions of the same polarity on the first face of the rotor disc.
摘要翻译：电磁制动器或离合器包括面对转子盘的第一面的第一面，所述盘安装成朝向和远离另一个运动; 以及定子线圈通电以将盘的第一面推离转子盘的第一面。在第一组旋转位置中，制动器或离合器盘的第一面上的一个极性的磁区面对转子盘的第一面上相反极性的磁性区域，并且在第二组旋转位置插入在第一组旋转位置的相应的一个之间的轴上，制动器或离合器盘的第一面上的一个极性的磁区面对转子盘的第一面上具有相同极性的磁性区域。

4. 发明申请

US20120037752A1 AIRCRAFT LANDING GEAR UNLOCK ACTUATOR 有权
公开(公告)号：US20120037752A1
公开(公告)日：2012-02-16
申请号：US12131996
申请日：2008-06-03
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： B64C25/26
CPC分类号： B64C25/26 , Y10T74/18672
摘要： This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. A lock-stay is connected to the landing gear strut and is movable between locked and unlocked conditions. An unlock actuator is connected to the lock-stay and includes first and second members movable relative to one another. The first member is movable between first and second positions that correspond to the locked and unlocked conditions. A controller is in communication with the unlock actuator and is configured to command the unlock actuator between the first and second positions in response to an input. The second member is permitted to free-drive relative to the first member between the stowed and deployed positions with the lock-stay in the unlocked condition.

5. 发明授权

US08070094B2 Aircraft landing gear actuator 有权
标题翻译：飞机起落架执行器
公开(公告)号：US08070094B2
公开(公告)日：2011-12-06
申请号：US12174038
申请日：2008-07-16
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： B64C25/12
CPC分类号： B64C25/24 , B64C25/12 , B64C25/30 , F16H25/205 , F16H25/2454 , F16H2025/2071 , F16H2025/2081 , H02K7/06
摘要： A landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. An actuator is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller in communication with the actuator is configured to command the actuator between the stowed and deployed positions in response to an input. The controller commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive.
摘要翻译：起落架系统，其包括可在收起位置和展开位置之间旋转的起落架支柱。致动器连接到起落架支柱，并且包括容纳在共同体内并可彼此独立操作的主和应急驱动器。与致动器通信的控制器被配置为响应于输入而在致动器和收起位置之间指令致动器。控制器在正常运行状态下命令主驱动器，并在主驱动器的故障状态下命令紧急驱动器。致动器包括支撑紧急的主体和彼此同轴布置的主导螺杆。主电机和应急电动机分别连接到主和应急丝杠。输出杆由主体支撑并延伸。输出杆螺纹连接到主导螺杆上并且与主导螺杆同轴并且构造成响应于主丝杠的旋转而轴向移动。制动器选择性地启用和禁用应急驱动器。

6. 发明授权

US10309225B2 Actuator for use in a rotor blade 有权
公开(公告)号：US10309225B2
公开(公告)日：2019-06-04
申请号：US13700282
申请日：2011-05-27
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： F01D5/12 , B64C27/615 , B64C27/72
摘要： A rotor blade includes an actuator comprising an electric motor having a rotary drive shaft, a bearing for mounting the rotary drive shaft along an axis extending along the length of the rotor blade, and a lubrication system for lubricating the bearing. The lubrication system includes a sump closer to the tip of the blade than the bearing, and a pump for pumping lubricant from the sump to the bearing.

7. 发明授权

US08292219B2 Aircraft landing gear unlock actuator 有权
标题翻译：飞机起落架解锁执行器
公开(公告)号：US08292219B2
公开(公告)日：2012-10-23
申请号：US13404174
申请日：2012-02-24
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： B64C25/26
CPC分类号： B64C25/26 , Y10T74/18672
摘要： This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. A lock-stay is connected to the landing gear strut and is movable between locked and unlocked conditions. An unlock actuator is connected to the lock-stay and includes first and second members movable relative to one another. The first member is movable between first and second positions that correspond to the locked and unlocked conditions. A controller is in communication with the unlock actuator and is configured to command the unlock actuator between the first and second positions in response to an input. The second member is permitted to free-drive relative to the first member between the stowed and deployed positions with the lock-stay in the unlocked condition.
摘要翻译：本公开涉及一种起落架系统，其包括可在收起位置和展开位置之间旋转的起落架支柱。锁定支架连接到起落架支柱，并且可在锁定和解锁状态之间移动。解锁致动器连接到锁定支架，并且包括可相对于彼此移动的第一和第二构件。第一构件可在对应于锁定和解锁状态的第一和第二位置之间移动。控制器与解锁致动器通信，并且被配置为响应于输入而在第一和第二位置之间命令解锁致动器。允许第二构件在收起位置和展开位置之间相对于第一构件自由驱动，在锁定状态下保持锁定。

8. 发明申请

US20100012779A1 AIRCRAFT LANDING GEAR ACTUATOR 有权
标题翻译：飞机接地齿轮执行器
公开(公告)号：US20100012779A1
公开(公告)日：2010-01-21
申请号：US12174038
申请日：2008-07-16
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： B64C25/10 , H02K7/00
CPC分类号： B64C25/24 , B64C25/12 , B64C25/30 , F16H25/205 , F16H25/2454 , F16H2025/2071 , F16H2025/2081 , H02K7/06
摘要： This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. An actuator is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller in communication with the actuator is configured to command the actuator between the stowed and deployed positions in response to an input. The controller commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive.
摘要翻译：本公开涉及一种起落架系统，其包括可在收起位置和展开位置之间旋转的起落架支柱。致动器连接到起落架支柱，并且包括容纳在共同体内并可彼此独立操作的主和应急驱动器。与致动器通信的控制器被配置为响应于输入而在致动器和收起位置之间指令致动器。控制器在正常运行状态下命令主驱动器，并在主驱动器的故障状态下命令紧急驱动器。致动器包括支撑紧急的主体和彼此同轴布置的主导螺杆。主电机和应急电动机分别连接到主和应急丝杠。输出杆由主体支撑并延伸。输出杆螺纹连接到主导螺杆上并且与主导螺杆同轴并且构造成响应于主丝杠的旋转而轴向移动。制动器选择性地启用和禁用应急驱动器。

9. 发明申请

US20130272873A1 Actuator for Use in a Rotor Blade 审中-公开
标题翻译：用于转子叶片的执行器
公开(公告)号：US20130272873A1
公开(公告)日：2013-10-17
申请号：US13700282
申请日：2011-05-27
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： F01D5/12
CPC分类号： F01D5/12 , B64C27/615 , B64C2027/7272 , Y02T50/34
摘要： A rotor blade includes an actuator comprising an electric motor having a rotary drive shaft, a bearing for mounting the rotary drive shaft along an axis extending along the length of the rotor blade, and a lubrication system for lubricating the bearing. The lubrication system includes a sump closer to the tip of the blade than the bearing, and a pump for pumping lubricant from the sump to the bearing.
摘要翻译：转子叶片包括具有旋转驱动轴的电动机的致动器，用于沿转子叶片的长度延伸的轴线安装旋转驱动轴的轴承以及用于润滑轴承的润滑系统。润滑系统包括比轴承更靠近叶片尖端的油槽，以及用于将润滑剂从油底壳泵送到轴承的泵。

10. 发明申请

US20120145827A1 AIRCRAFT LANDING GEAR UNLOCK ACTUATOR 有权
标题翻译：飞机接地齿轮解锁器
公开(公告)号：US20120145827A1
公开(公告)日：2012-06-14
申请号：US13404174
申请日：2012-02-24
申请人： Andrew John Collins
发明人： Andrew John Collins
IPC分类号： B64C25/26
CPC分类号： B64C25/26 , Y10T74/18672
摘要： This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. A lock-stay is connected to the landing gear strut and is movable between locked and unlocked conditions. An unlock actuator is connected to the lock-stay and includes first and second members movable relative to one another. The first member is movable between first and second positions that correspond to the locked and unlocked conditions. A controller is in communication with the unlock actuator and is configured to command the unlock actuator between the first and second positions in response to an input. The second member is permitted to free-drive relative to the first member between the stowed and deployed positions with the lock-stay in the unlocked condition.
摘要翻译：本公开涉及一种起落架系统，其包括可在收起位置和展开位置之间旋转的起落架支柱。锁定支架连接到起落架支柱，并且可在锁定和解锁状态之间移动。解锁致动器连接到锁定支架，并且包括可相对于彼此移动的第一和第二构件。第一构件可在对应于锁定和解锁状态的第一和第二位置之间移动。控制器与解锁致动器通信，并且被配置为响应于输入而在第一和第二位置之间命令解锁致动器。允许第二构件在收起位置和展开位置之间相对于第一构件自由驱动，在锁定状态下保持锁定。

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