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公开(公告)号：US20160200430A1
公开(公告)日：2016-07-14
申请号：US14286197
申请日：2014-05-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Corey Dickman , Carlos A. Fenny , David Schultz
CPC classification number: B64C13/503 , B64C27/14 , B64C27/82
Abstract: In some embodiments, an actuation system includes a an actuator assembly, a yoke, and a control rod. The actuator assembly comprises a first actuator. The first actuator is configured to extend in a first direction and retract in a second direction opposite of the first direction. The yoke is coupled to the first actuator at a first actuator end proximate to the first direction. The control rod is coupled to the yoke at a first control rod end and extends in the second direction past the actuator assembly to a second end in mechanical communication with an output device.
Abstract translation: 在一些实施例中，致动系统包括致动器组件，轭架和控制杆。 致动器组件包括第一致动器。 第一致动器构造成在第一方向上延伸并且沿与第一方向相反的第二方向缩回。 在靠近第一方向的第一致动器端处，轭被耦合到第一致动器。 控制杆在第一控制杆端处联接到轭，并且在第二方向上延伸超过致动器组件到与输出装置机械连通的第二端。
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公开(公告)号：US09156545B1
公开(公告)日：2015-10-13
申请号：US13949698
申请日：2013-07-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos A. Fenny , Troy Schank , Frank B. Stamps
CPC classification number: B64C27/30 , B64C11/28 , B64C27/32 , B64C27/41 , B64C27/50 , B64C27/52 , B64C27/605 , B64C27/615 , B64C29/0033
Abstract: According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.
Abstract translation: 根据一个实施例，转子叶片旋转系统包括轮毂，转子叶片，其与轮毂机械连通并可围绕旋转轴线旋转，斜盘，俯仰杆和致动器。 旋转斜盘包括旋转部分和非旋转部分。 节距连杆联接到旋转斜盘的旋转部分并且与转子叶片机械连通。 致动器联接到旋转斜盘的非旋转部分并且可操作以将斜盘从第一位置重新定位到第二位置，使得俯仰杆将转子叶片从展开位置枢转到折叠位置。
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公开(公告)号：US20180111680A1
公开(公告)日：2018-04-26
申请号：US15298959
申请日：2016-10-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos A. Fenny , Daniel B. Robertson , Kirk L. Groninga , Troy C. Schank
CPC classification number: B64C27/025 , B64C27/18 , B64C27/82 , B64C2027/8209 , B64C2027/8236 , B64D27/02 , B64D27/24 , B64D2027/026 , B64F1/362 , Y02T50/44 , Y02T50/64
Abstract: A rotorcraft capable of a hover mode and a forward cruise mode including a fuselage, a first electric propulsion system, a second electric propulsion system, and an electric power control unit to control power to the first and second electric propulsion systems in the hover and forward cruise modes. The first electric propulsion system is a tip jet cold flow system that imparts rotation on a pair of rotor blades disposed above a top surface of the fuselage, and a first electric motor configured to drive the tip jet cold flow system. The second electric propulsion system includes a propeller disposed in the rear of the fuselage and a second electric motor configured to drive the propeller.
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公开(公告)号：US09889929B2
公开(公告)日：2018-02-13
申请号：US14038154
申请日：2013-09-26
Applicant: Bell Helicopter Textron Inc.
Inventor： Charles Eric Covington , Carlos A. Fenny
CPC classification number: B64C27/64 , B64C27/605 , H01F7/066 , H01F7/122 , H02K7/003
Abstract: According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a first magnetic material, a shaft, and a first non-magnetic material. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components.
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公开(公告)号：US09815553B2
公开(公告)日：2017-11-14
申请号：US13932407
申请日：2013-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： James M. McCollough , Carlos A. Fenny
Abstract: According to some embodiments, a rotorcraft includes a secondary rotor control system located proximate to the empennage of the rotorcraft. The secondary rotor control system includes at least one hydraulic pump and at least one hydraulic actuator. The at least one hydraulic pump is located proximate to the empennage. The at least one hydraulic actuator is located proximate to the empennage and configured to adjust at least one operating characteristic of the at least one secondary rotor blade.
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Patent Agency Ranking
公开(公告)号：US09290266B2
公开(公告)日：2016-03-22
申请号：US14202826
申请日：2014-03-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel B. Robertson , Dudley E. Smith , Carlos A. Fenny , Walter West Riley
Abstract: A speed control assembly includes an input drive shaft coupled to a first gear subassembly having a rotatable gear, a second gear subassembly coupled to an output drive shaft, and a linkage coupling the first and second gear subassemblies, wherein the input drive shaft, the first and second gear subassemblies, and the linkage are configured such that a rotational speed of the rotatable gear adjusts a ratio of a rotational speed of the output drive shaft to a rotational speed of the output drive shaft. In some embodiments, the first gear subassembly includes a sun gear coupled to the input drive shaft, one or more planet gears, and a ring gear as the rotatable gear. In some embodiments, the second gear subassembly includes a sun gear coupled to the output drive shaft, one or more planet gears, and a fixed ring gear.
Abstract translation: 速度控制组件包括联接到具有可旋转齿轮的第一齿轮子组件的输入驱动轴，联接到输出驱动轴的第二齿轮子组件和联接第一和第二齿轮组件的联动器，其中输入驱动轴，第一 和二档组件，并且所述连杆构造成使得所述可旋转齿轮的旋转速度调节所述输出驱动轴的旋转速度与所述输出驱动轴的旋转速度的比率。 在一些实施例中，第一齿轮子组件包括联接到输入驱动轴，一个或多个行星齿轮和作为可旋转齿轮的齿圈的太阳齿轮。 在一些实施例中，第二齿轮子组件包括联接到输出驱动轴，一个或多个行星齿轮和固定齿圈的太阳齿轮。
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公开(公告)号：US20150274287A1
公开(公告)日：2015-10-01
申请号：US14202826
申请日：2014-03-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel B. Robertson , Dudley E. Smith , Carlos A. Fenny , Walter West Riley
Abstract: A speed control assembly includes an input drive shaft coupled to a first gear subassembly having a rotatable gear, a second gear subassembly coupled to an output drive shaft, and a linkage coupling the first and second gear subassemblies, wherein the input drive shaft, the first and second gear subassemblies, and the linkage are configured such that a rotational speed of the rotatable gear adjusts a ratio of a rotational speed of the output drive shaft to a rotational speed of the output drive shaft. In some embodiments, the first gear subassembly includes a sun gear coupled to the input drive shaft, one or more planet gears, and a ring gear as the rotatable gear. In some embodiments, the second gear subassembly includes a sun gear coupled to the output drive shaft, one or more planet gears, and a fixed ring gear.
Abstract translation: 速度控制组件包括联接到具有可旋转齿轮的第一齿轮子组件的输入驱动轴，联接到输出驱动轴的第二齿轮子组件和联接第一和第二齿轮组件的联动器，其中输入驱动轴，第一 和二档组件，并且所述连杆构造成使得所述可旋转齿轮的旋转速度调节所述输出驱动轴的旋转速度与所述输出驱动轴的旋转速度的比率。 在一些实施例中，第一齿轮子组件包括联接到输入驱动轴，一个或多个行星齿轮和作为可旋转齿轮的齿圈的太阳齿轮。 在一些实施例中，第二齿轮子组件包括联接到输出驱动轴，一个或多个行星齿轮和固定齿圈的太阳齿轮。
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公开(公告)号：US20150217866A1
公开(公告)日：2015-08-06
申请号：US14482583
申请日：2014-09-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Pasquale Spina , Carlos A. Fenny , Jean-Sebastian Plante
CPC classification number: F16D37/008 , B64C13/28 , B64C27/08 , B64C27/12 , B64C27/56 , B64C27/605 , B64C27/64 , B64C27/68 , B64C27/78 , B64D31/14 , B64D35/02 , B64D35/04 , F16D27/14 , F16D37/02 , F16D2037/001 , F16D2037/007 , F16H25/20 , F16H2025/2059 , Y02T50/44 , Y10T74/18704
Abstract: In some embodiments, a rotorcraft flight control actuator includes a driving member configured to receive mechanical energy from a power source, a driven member, a magnetorheological (MR) fluid disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member, an output member configured to be coupled between the driven member and a flight control device of a rotor system, and a magnetic circuit configured to deliver a magnetic field towards the MR fluid, the magnetic circuit configured to vary the strength of the magnetic field in response to inputs.
Abstract translation: 在一些实施例中，旋翼航空器飞行控制致动器包括驱动构件，其构造成从动力源，从动构件，设置在驱动构件和从动构件之间的磁流变（MR）流体接收机械能，并且构造成传递可变量 从驱动构件到从动构件的机械能，构造成联接在从动构件和转子系统的飞行控制装置之间的输出构件，以及被配置为向MR流体输送磁场的磁路，磁路 被配置为响应于输入而改变磁场的强度。
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公开(公告)号：US08967552B2
公开(公告)日：2015-03-03
申请号：US13655778
申请日：2012-10-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Charles E. Covington , Carlos A. Fenny , Brady G. Atkins
IPC: B64C13/40 , B64C27/59 , B64C27/605 , B64C27/00
CPC classification number: B64C27/59 , B64C27/605 , B64C2027/004 , Y10T74/18056
Abstract: According to one embodiment, a stability augmentation system includes a master linkage, a stability augmentation motor, and three linkages. A first linkage is coupled to the master linkage and operable to receive movements representative of pilot commands from a pilot command system. A second linkage is coupled between the stability augmentation motor and the master linkage and operable to receive movements representative of augmentation commands from the stability augmentation motor. A third linkage is coupled to the master linkage and operable to transmit movements representative of blade position commands to a blade control system in response to the movements representative of pilot commands and the movements representative of augmentation commands.
Abstract translation: 根据一个实施例，稳定性增强系统包括主联动装置，稳定性增加电动机和三个联动装置。 第一联动装置耦合到主联动装置并且可操作以从导向指令系统接收代表导向指令的运动。 第二联动装置耦合在稳定性增强电动机和主联动装置之间，并且可操作以从稳定性增强电动机接收代表增强指令的运动。 第三联动装置联接到主联动装置并且可操作以响应于代表导向命令的运动和代表增加命令的运动而将代表刀片位置命令的运动传送到刀片控制系统。
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30.发明申请公开(公告)号：US20150001337A1
公开(公告)日：2015-01-01
申请号：US13932407
申请日：2013-07-01
Applicant: Bell Helicopter Textron Inc.
Inventor： James M. McCollough , Carlos A. Fenny
Abstract: According to some embodiments, a rotorcraft includes a secondary rotor control system located proximate to the empennage of the rotorcraft. The secondary rotor control system includes at least one hydraulic pump and at least one hydraulic actuator. The at least one hydraulic pump is located proximate to the empennage. The at least one hydraulic actuator is located proximate to the empennage and configured to adjust at least one operating characteristic of the at least one secondary rotor blade.
Abstract translation: 根据一些实施例，旋翼航空器包括位于旋翼航空器的尾翼附近的次级转子控制系统。 次级转子控制系统包括至少一个液压泵和至少一个液压致动器。 至少一个液压泵位于尾翼附近。 所述至少一个液压致动器位于所述尾翼附近并且被构造成调节所述至少一个次级转子叶片的至少一个操作特性。
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