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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：US20180057148A1
公开(公告)日：2018-03-01
申请号：US15252560
申请日：2016-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Bosworth
CPC classification number: B64C13/18 , B64C3/385 , B64C29/0033
Abstract: A tiltrotor aircraft includes a fuselage supporting first and second wings each having an outboard end. First and second nacelles are respectively coupled to the outboard ends of the first and second wings. The first and second nacelles each have an outboard end. First and second wing extensions are rotatably coupled, respectively, to the outboard ends of the first and second nacelles. First and second actuators are operable to respectively move the first and second wing extensions to dampen a mode of the first and second wings, thereby stabilizing the tiltrotor aircraft.
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Patent Agency Ranking
公开(公告)号：US20190228665A1
公开(公告)日：2019-07-25
申请号：US15877513
申请日：2018-01-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Bosworth
Abstract: Systems, methods and non-transitory computer readable storage media for airspace management within an airspace region at a node of a peer to peer network having a plurality of nodes and maintaining a blockchain containing a current deconflicted flight schedule for the airspace region. One method includes receiving requests for airspace reservations, each including flight plan data, from other nodes over the peer to peer network, compiling the flight plan data to identify conflicts between the requests and the current deconflicted flight schedule, validating the flight plan data of the requests that do not conflict with the current deconflicted flight schedule to generate validated airspace reservations, creating a block containing the validated airspace reservations and interlinking the block with the blockchain such that the blockchain contains a new deconflicted flight schedule for the airspace region for broadcast to the other nodes over the peer to peer network.
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公开(公告)号：US20190002078A1
公开(公告)日：2019-01-03
申请号：US15638345
申请日：2017-06-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Clement Parham, Jr. , Jeffrey Bosworth , Gary Miller , Frank Bradley Stamps , Jouyoung Jason Choi , Paul K. Oldroyd , Richard Erler Rauber , Michael Scott Seifert
Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly. The damping sublayer reduces the deflection of the wing, thereby stabilizing the wing during forward flight
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公开(公告)号：US10906632B2
公开(公告)日：2021-02-02
申请号：US15987059
申请日：2018-05-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Bosworth
Abstract: In one embodiment, a method is performed by a control computer. The method includes receiving a time series of control inputs in relation to a control axis of an aircraft, where the control computer causes actuation in response to each control input in the time series as the control input is received. The method also includes determining aircraft oscillation over a sample period corresponding to the time series. The method also includes evaluating information related to the determined aircraft oscillation using engagement settings associated with a control filter. The method also includes engaging the control filter responsive to the information satisfying the engagement settings, where the engaged control filter systematically attenuates future control inputs in relation to the control axis prior to actuation responsive thereto.
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公开(公告)号：US10279892B2
公开(公告)日：2019-05-07
申请号：US15252560
申请日：2016-08-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Bosworth
Abstract: A tiltrotor aircraft includes a fuselage supporting first and second wings each having an outboard end. First and second nacelles are respectively coupled to the outboard ends of the first and second wings. The first and second nacelles each have an outboard end. First and second wing extensions are rotatably coupled, respectively, to the outboard ends of the first and second nacelles. First and second actuators are operable to respectively move the first and second wing extensions to dampen a mode of the first and second wings, thereby stabilizing the tiltrotor aircraft.
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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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