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公开(公告)号：US20190233096A1
公开(公告)日：2019-08-01
申请号：US15882287
申请日：2018-01-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Tyler Wayne BALDWIN , Kyle Thomas CRAVENER , Andrew MARESH
Abstract: A tri-hybrid yoke including a center ring connected to a CF fitting connected to flexure arms. An inboard centrifugal force bearing assembly connects to the CF fitting and a grip. An outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center ring and the CF fittings carry the centrifugal force at a position inboard of the flexure arm.
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公开(公告)号：US20190225321A1
公开(公告)日：2019-07-25
申请号：US15880216
申请日：2018-01-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Stephen Yibum Chung , Matthew E. Louis
Abstract: One embodiment is a method including defining a maximum deflection for a first axis of a control surface axis of an aircraft; defining a maximum deflection for a second axis of the control surface; and creating a graphical representation of the maximum deflection for the first and second control surface axes. The method further includes determining an angle of rotation of a structure on which the control surface is carried, wherein the angle of rotation is relative to a body of the aircraft; rotating the graphical representation in accordance with the determined angle of rotation; calculating a distance between a point representing a selected combination of roll moment and yaw moment and each edge of the graphical representation; and calculating a control surface deflection based on the calculated distances.
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公开(公告)号：US20190225316A1
公开(公告)日：2019-07-25
申请号：US15878329
申请日：2018-01-23
Applicant: Bell Helicopter Textron Inc.
Inventor： Yann Lavallee
Abstract: Systems and methods include providing an aircraft with a fuselage, an airframe that provides structural rigidity to the fuselage, and at least one door that allows access to an interior of the fuselage through an opening in the fuselage. The aircraft includes an overlapping, tongue and groove door interface formed between a frame of the door and a portion of the airframe that at least partially borders the opening in the fuselage. At least a portion of the airframe includes a concavity. At least a portion of the door frame includes a complementary shaped profile to the concavity of the airframe. The complementary profile of the door frame and the concavity of the airframe form a seal between the door frame and the airframe when the complementary portion is at least partially received within the concavity by selectively rotating the door to its closed position.
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公开(公告)号：US10343787B2
公开(公告)日：2019-07-09
申请号：US15788039
申请日：2017-10-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Alison Ann Davis , Charles Speller
Abstract: A rotor system including a hub; a rim configured to rotate about the hub, the rim including an interior surface and an engagement surface; a plurality of rotor blades extending from the hub and coupled to the interior surface of the rim; and one or more outer drive gears disposed adjacent to the engagement surface of the rim; each of the one or more outer drive gears including a plurality of teeth for engaging the engagement surface of the rim; wherein the one or more outer drive gears are configured to rotate the rim such that the plurality of rotor blades rotates about the hub. Other aspects provide an aircraft rotor system and methods of operating an aircraft rotor system.
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公开(公告)号：US10328658B2
公开(公告)日：2019-06-25
申请号：US14982243
申请日：2015-12-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Phillip Kendrick , Levi Armstrong , Paul K. Oldroyd , Dave Carlson
IPC: B32B3/12 , B32B37/10 , B32B37/06 , B32B3/30 , B32B5/02 , B32B5/12 , B32B5/26 , B32B1/08 , B32B3/06 , B32B3/28 , B21D15/02 , B32B3/20 , B32B3/10
Abstract: A composite core with non-traditional geometries includes multiple elongate tubes arranged in a two-dimensional array. Each tube is made of a composite material. Each tube includes multiple curved sides. Each curved side inwardly curves toward a longitudinal axis passing through a geometric center of the tube to form a valley on an outer surface of the tube. An end of a first curved side connects to an end of a second curved side to form a crest on the outer surface of the tube. At least one crest formed on an outer surface of a first tube in the two-dimensional array contacts at least one valley formed on an outer surface of an adjacent second tube in the two-dimensional array.
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Patent Agency Ranking
公开(公告)号：US20190185142A1
公开(公告)日：2019-06-20
申请号：US15845967
申请日：2017-12-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Jared Mark Paulson , Tyler Wayne Baldwin , Kyle Thomas Cravener
Abstract: A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
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公开(公告)号：US20190184646A1
公开(公告)日：2019-06-20
申请号：US15842248
申请日：2017-12-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Drew Alan Sutton , Paul K. Oldroyd
CPC classification number: B29C65/06 , B29C65/00 , B29C65/02 , B29C65/022 , B29C65/026 , B29C65/04 , B29C65/1403 , B29C65/1432 , B29C65/32 , B29C66/721 , B29C66/73115 , B29C66/73921 , B29D99/001 , B29K2101/12 , B29L2031/3082 , B29L2031/3085 , B32B7/04 , B64C1/12 , B64C3/26
Abstract: Systems and methods of constructing a thermoplastic component include joining a thermoplastic skin to a thermoplastic core by introducing heat at an interface of each of the thermoplastic skin and the thermoplastic core to at least partially melt the thermoplastic skin to a thermoplastic core at the interfaces, applying pressure to at least one of the thermoplastic skin and the thermoplastic core to sandwich the elements, and cooling the interfaces below the melting point of each of the thermoplastic skin and the thermoplastic core to consolidate the thermoplastic skin and the thermoplastic core into a unitary thermoplastic component. An optional thermoplastic film may be disposed between the thermoplastic skin and the thermoplastic core. The thermoplastic skin may be joined to the thermoplastic core to form an intermediate thermoplastic component prior to joining the thermoplastic skin to the intermediate component.
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公开(公告)号：US20190161182A1
公开(公告)日：2019-05-30
申请号：US15962889
申请日：2018-04-25
Applicant: Bell Helicopter Textron Inc.
Inventor： Jillian Samantha Alfred , Luke Dafydd Gillett , Bradley Don Linton , Robert Earl Worsham, II
Abstract: A rotorcraft including a control element, a control sensor connected to the control element, where the control sensor is operable to generate trim data indicating a displacement of the control element in relation to a trim position of the control element, and a flight control computer (FCC) operable to monitor the trim data and determine an active detent state of the control element. The active detent state is one of an in-detent state, an out-of-detent state, and an in-transition state. The FCC is operable to buffer a transition of the active detent state from the in-detent state to the out-of-detent state using the in-transition state. The FCC provides a first flight management function when the active detent state is the in-detent state or the in-transition state, and provides a second flight management function when the active detent state is the out-of-detent state.
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公开(公告)号：US20190161181A1
公开(公告)日：2019-05-30
申请号：US15940184
申请日：2018-03-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Jillian Samantha Alfred , Monica Sibello , Robert Earl Worsham, II
Abstract: A rotorcraft having a plurality of wheels, each wheel configured to receive weight of the rotorcraft when in contact with a landing surface, a plurality of wheel sensors, each wheel sensor associated with a respective wheel and having circuitry configured to generate a wheel on ground (WOG) signal indicating that the respective wheel is in contact with the landing surface, and a flight control computer (FCC) in signal communication with the plurality of wheel sensors, the FCC operable to execute a first hold loop having a first integrator and providing first control augmentation of a rotorcraft flight system, the FCC further operable to freeze the first integrator according to a number of WOG signals received from the plurality of wheel sensors, the FCC further operable to generate a first control signal according to a first value provided by the first integrator while the first integrator is frozen.
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公开(公告)号：US20190154106A1
公开(公告)日：2019-05-23
申请号：US15820129
申请日：2017-11-21
Applicant: Bell Helicopter Textron Inc.
Inventor： David E. Heverly, II
IPC: F16F15/023 , B64C29/00 , B06B1/18
Abstract: In one embodiment, a centrifugal force generating device comprises a first hydraulic rotor, a second hydraulic rotor, and one or more hydraulic control valves. The first hydraulic rotor comprises a first mass and is configured to rotationally drive the first mass around a first axis of rotation using a first flow of hydraulic fluid through the first hydraulic rotor. The second hydraulic rotor comprises a second mass and is configured to rotationally drive the second mass around a second axis of rotation using a second flow of hydraulic fluid through the second hydraulic rotor. The one or more hydraulic control valves are configured to control the first flow of hydraulic fluid through the first hydraulic rotor and the second flow of hydraulic fluid through the second hydraulic rotor.
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