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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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Patent Agency Ranking
公开(公告)号：US20150122953A1
公开(公告)日：2015-05-07
申请号：US14069425
申请日：2013-11-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Burnett , Christopher Foskey , Joel McIntyre
CPC classification number: F16H21/00 , B64C27/22 , B64C27/33 , B64C27/35 , B64C29/0033 , F16C19/30 , F16C27/063 , F16D3/62 , F16F1/3849 , F16F1/387 , F16F1/393 , Y10T74/20006
Abstract: According to one embodiment, a drive link includes a first bearing housing, a second bearing housing, and a central portion coupled between the first bearing housing and the second bearing housing. The central portion has less torsional stiffness than the first and second bearing housings such that the central portion twists in response to cocking of the first bearing housing relative to the second bearing housing.
Abstract translation: 根据一个实施例，驱动连杆包括第一轴承壳体，第二轴承壳体和联接在第一轴承壳体和第二轴承壳体之间的中心部分。 中心部分具有比第一和第二轴承壳体更小的扭转刚度，使得中心部分响应于第一轴承壳体相对于第二轴承壳体的翘起而扭转。
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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：US20150034772A1
公开(公告)日：2015-02-05
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: According to one embodiment, a composite flexure may secure a rotor blade to a yoke in a tiltrotor rotor system. The composite flexure includes a composite body, a first end configured to couple the composite member to the yoke, and a second end configured to couple the composite member to the rotor blade.
Abstract translation: 根据一个实施例，复合挠曲件可将转子叶片固定在倾斜转子转子系统中的轭。 复合挠曲件包括复合体，构造成将复合构件耦合到轭的第一端，以及构造成将复合构件耦合到转子叶片的第二端。
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公开(公告)号：US10239604B2
公开(公告)日：2019-03-26
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
IPC: B64C11/26 , B64C29/00 , B64C11/24 , B64C27/473
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：US09657816B2
公开(公告)日：2017-05-23
申请号：US14069425
申请日：2013-11-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Burnett , Christopher Foskey , Joel McIntyre
IPC: B64C27/32 , F16H21/00 , B64C27/33 , B64C27/35 , F16D3/62 , F16F1/387 , F16F1/393 , B64C27/22 , F16C19/30 , F16C27/06 , B64C29/00
CPC classification number: F16H21/00 , B64C27/22 , B64C27/33 , B64C27/35 , B64C29/0033 , F16C19/30 , F16C27/063 , F16D3/62 , F16F1/3849 , F16F1/387 , F16F1/393 , Y10T74/20006
Abstract: A drive link includes a first bearing housing, a second bearing housing, and a central portion coupled between the first bearing housing and the second bearing housing. The central portion includes a central radial bearing configured such that the central portion twists in response to cocking of the first bearing housing relative to the second bearing housing.
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