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公开(公告)号：US09499262B2
公开(公告)日：2016-11-22
申请号：US13958192
申请日：2013-08-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Frank B. Stamps , Joel McIntyre , Gary Miller
CPC classification number: B64C27/33 , B64C27/48 , B64C29/0033
Abstract: A composite flexure that secures a rotor blade to a gimbaled yoke in a tiltrotor rotor system. The composite flexure includes a composite flexure member, a first end, and a second end. The first end of the composite flexure couples the composite flexure to the gimbaled yoke, and the second end of the composite flexure couples the composite flexure to the rotor blade. The composite flexure is twisted when the composite flexure is not subject to torsional loads in order to accommodate various forces imparted on the rotor system.
Abstract translation: 复合弯曲，其将转子叶片固定在倾斜旋转器转子系统中的万向轭。 复合挠曲件包括复合挠曲构件，第一端和第二端。 复合挠曲件的第一端将复合挠曲件联接到万向架轭架上，并且复合挠曲件的第二端将复合挠曲件联接到转子叶片。 当复合挠曲件不受扭转载荷的影响时，复合挠曲是扭转的，以适应转子系统上施加的各种力。
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公开(公告)号：US09399513B2
公开(公告)日：2016-07-26
申请号：US13673475
申请日：2012-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Drew A. Sutton , Christopher Foskey , Dudley Smith , Frank B. Stamps
Abstract: According to one embodiment, a constant velocity (CV) joint includes a first yoke, a second yoke, and a control mechanism. The first yoke is configured to be rotatably coupled to an input device about a first axis and configured to receive the input device through a first opening. The second yoke is rotatably coupled to the first yoke about a second axis and rotatably coupled to an output device about a third axis. The control mechanism is adapted to constrain the first yoke and the second yoke so as to achieve a substantially CV characteristic between the input device and the output device.
Abstract translation: 根据一个实施例，等速（CV）接头包括第一磁轭，第二磁轭和控制机构。 第一磁轭被配置成围绕第一轴线可旋转地联接到输入装置，并且被配置成通过第一开口接收输入装置。 第二轭被围绕第二轴可旋转地联接到第一轭，并且围绕第三轴可旋转地联接到输出装置。 控制机构适于约束第一磁轭和第二磁轭，以便在输入装置和输出装置之间实现基本的CV特性。
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公开(公告)号：US20160075430A1
公开(公告)日：2016-03-17
申请号：US14485967
申请日：2014-09-15
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Christopher Foskey , Frank B. Stamps
IPC: B64C27/46 , B64C27/473
CPC classification number: B64C27/463 , B64C27/473
Abstract: A rotor blade system includes a rotor blade having an outboard section and an inboard section, a hinge joint rigidly attached to the outboard section, and an adhedral tip engaged with the hinge joint. A method includes pivotally attaching an adhedral tip to the rotor blade and pivoting the adhedral tip during flight to change the flight performance characteristics of the blade during flight.
Abstract translation: 转子叶片系统包括具有外侧部分和内侧部分的转子叶片，刚性地附接到外侧部分的铰链接头以及与铰链接合部相接合的内接尖端。 一种方法包括将飞散的顶端枢转地连接到转子叶片上，并且在飞行期间枢转该内向尖端以改变飞行中叶片的飞行性能特征。
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公开(公告)号：US20140271223A1
公开(公告)日：2014-09-18
申请号：US13828495
申请日：2013-03-14
Applicant: BELL HELICOPTER TEXTRON INC.
Inventor： Christopher Foskey , Frank B. Stamps , Richard Rauber
IPC: B64C11/14
CPC classification number: B64C11/14 , B64C29/0033 , Y10T29/49316
Abstract: An apparatus comprising a spinner fairing assembly comprising a spinner configured to be fixed relative to a gimbaled yoke coupled to a mast system, and a spinner base configured to be fixed relative to the mast system. A spinner fairing assembly comprising a spinner aligned along a first axis, and a spinner base aligned along a second axis and configured to interface with the spinner, wherein the spinner is configured to transition between a neutral position and a canted position with respect to the spinner base, wherein the first axis and the second axis are coincident in the neutral position, and wherein the first axis and the second axis are not coincident and meet at an origin within the spinner in the canted position.
Abstract translation: 一种包括旋转整流罩组件的装置，其包括被配置为相对于连接到桅杆系统的万向架轭固定的旋转器，以及被配置为相对于所述桅杆系统固定的旋转底座。 一种旋转整流罩组件，包括沿着第一轴线对准的旋转器，以及沿着第二轴线对准并配置成与所述旋转器相接合的旋转器基座，其中所述旋转器构造成相对于所述旋转器在中性位置和倾斜位置之间转换 底座，其中所述第一轴线和所述第二轴线在所述中立位置重合，并且其中所述第一轴线和所述第二轴线不重合，并且在所述旋转器中在所述倾斜位置处在所述旋转器内的原点处相交。
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公开(公告)号：US10822954B2
公开(公告)日：2020-11-03
申请号：US16170414
申请日：2018-10-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Paul K. Oldroyd , Drew Sutton , Andrew Maresh , Christopher Foskey
IPC: B64C27/473 , F01D5/14
Abstract: A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.
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Patent Agency Ranking
公开(公告)号：US20170334548A1
公开(公告)日：2017-11-23
申请号：US15161215
申请日：2016-05-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Michael Burnett , Jeffrey Bosworth , Jared Mark Paulson , Joel McIntyre , Paul K. Oldroyd
CPC classification number: B64C11/26 , B64C11/24 , B64C27/473 , B64C29/0033 , B64C2027/4736
Abstract: A tiltrotor aircraft includes a fuselage, a wing member extending from the fuselage, an engine disposed relative to the wing member and a proprotor mechanically coupled to the engine. The proprotor includes a plurality of proprotor blade assemblies each including a spar and a sheath extending spanwise along the spar forming the leading edge of the proprotor blade assembly. The spar has a root section, a main section and a tip section. The spar has a generally oval cross section at radial stations along the main section and a first edge having a structural bias relative to a generally oppositely disposed second edge at the radial stations along the main section.
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公开(公告)号：US20170327205A1
公开(公告)日：2017-11-16
申请号：US15156224
申请日：2016-05-16
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Paul K. Oldroyd , Christopher Foskey
CPC classification number: B64C11/28 , B64C11/26 , B64C27/473 , B64C27/50 , B64C29/0033 , B64C2027/4736
Abstract: A tiltrotor aircraft includes a fuselage, a wing member extending from the fuselage, an engine disposed relative to the wing member, a rotor hub assembly mechanically coupled to the engine and a plurality of proprotor blade assemblies rotatably mounted to the rotor hub assembly and operable for beamwise folding relative thereto. The proprotor blade assemblies each including a spar and a sheath extending spanwise along a leading edge of the spar. The spar has a root section, a main section and a tip section. The spar has a generally oval cross section at radial stations along the main section of the spar with the root section of the spar forming an integral tang assembly operable for coupling the spar to the rotor hub assembly.
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公开(公告)号：US20170009588A1
公开(公告)日：2017-01-12
申请号：US14792263
申请日：2015-07-06
Applicant: Bell Helicopter Textron Inc.
Inventor： Paul K. Oldroyd , Drew Sutton , Andrew Maresh , Christopher Foskey
IPC: F01D5/14
CPC classification number: F01D5/147 , B64C27/473
Abstract: A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.
Abstract translation: 旋翼飞船转子叶片组件包括延伸小于转子叶片组件的全跨度的短柱梁。 上皮肤部分基本上延伸到转子叶片组件的整个跨度。 较低的皮肤部分基本上延伸到转子叶片组件的整个跨度。 短柱梁定位在上皮肤部分和下皮肤部分之间。
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公开(公告)号：US09382001B2
公开(公告)日：2016-07-05
申请号：US14338531
申请日：2014-07-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Frank Bradley Stamps
Abstract: One example of a torque transfer system for a rotorcraft includes a first rotational joint connected to a rotorcraft rotary shaft. The first rotational joint receives a portion of a torque generated by rotation of the rotorcraft rotary shaft and transfers the portion of the torque to a rotorcraft rotating component. The torque transfer system also includes a second rotational joint of a different type connected to the rotorcraft rotary shaft. The second rotational joint receives a remainder of the torque generated by the rotation of the rotorcraft rotary shaft and transfers the remainder of the torque to the rotorcraft rotating component.
Abstract translation: 用于旋翼航空器的扭矩传递系统的一个示例包括连接到旋翼航空器旋转轴的第一旋转接头。 第一旋转接头接收由旋翼飞机旋转轴的旋转产生的扭矩的一部分，并将扭矩的一部分转移到旋翼飞机旋转部件。 扭矩传递系统还包括连接到旋翼航空旋转轴的不同类型的第二旋转接头。 第二旋转接头接收由旋翼飞船旋转轴的旋转产生的扭矩的剩余部分，并将剩余的扭矩传递到旋翼飞轮旋转部件。
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公开(公告)号：US20160023752A1
公开(公告)日：2016-01-28
申请号：US14338531
申请日：2014-07-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Foskey , Frank Bradley Stamps
Abstract: One example of a torque transfer system for a rotorcraft includes a first rotational joint connected to a rotorcraft rotary shaft. The first rotational joint receives a portion of a torque generated by rotation of the rotorcraft rotary shaft and transfers the portion of the torque to a rotorcraft rotating component. The torque transfer system also includes a second rotational joint of a different type connected to the rotorcraft rotary shaft. The second rotational joint receives a remainder of the torque generated by the rotation of the rotorcraft rotary shaft and transfers the remainder of the torque to the rotorcraft rotating component.
Abstract translation: 用于旋翼航空器的扭矩传递系统的一个示例包括连接到旋翼航空器旋转轴的第一旋转接头。 第一旋转接头接收由旋翼飞机旋转轴的旋转产生的扭矩的一部分，并将扭矩的一部分转移到旋翼飞机旋转部件。 扭矩传递系统还包括连接到旋翼航空旋转轴的不同类型的第二旋转接头。 第二旋转接头接收由旋翼飞船旋转轴的旋转产生的扭矩的剩余部分，并将剩余的扭矩传递到旋翼飞轮旋转部件。
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