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公开(公告)号：US10380810B2
公开(公告)日：2019-08-13
申请号：US15677506
申请日：2017-08-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Rodney Keith Hale
Abstract: A method, system, and device for diagnosing an anomaly of a monitored component in a drive train, the method including obtaining rotational information associated with the component; receiving original data indicating the toothmesh frequency of the drive train; filtering the original data to remove energy above the toothmesh frequency; interpolating the filtered original data to generate an integer number of samples per tooth passage; and generating an amplified differential coherence (ADC). In some embodiments, an amplified differential coherence gearbox arrangement value (ADCT) is generated.
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公开(公告)号：US10377470B2
公开(公告)日：2019-08-13
申请号：US15646894
申请日：2017-07-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Jillian Samantha Alfred
Abstract: A system and method for providing state comparison of redundant processors used, e.g. to control a rotor craft. A primary microprocessor is configured to receive input data from a position sensor and a flight condition sensor and determine therefrom a first desired control law state, and a secondary microprocessor is configured to receive input data from the position sensor and the flight condition sensor and determine therefrom a second desired control law state. The first desired control law state from the primary microprocessor and the second desired control law state from the secondary microprocessor are compared, and (a) the first desired control law state is entered when the first desired control law state and the second desired control law state match, and (b) a last known control law state is maintained when the first desired control law state and the second desired control law state do not match.
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公开(公告)号：US20190241252A1
公开(公告)日：2019-08-08
申请号：US16388993
申请日：2019-04-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Shyhpyng Jack Shue
CPC classification number: B64C13/22 , B64C13/04 , B64C13/20 , B64C29/0033 , B64D45/0015 , B64D45/0031 , B64D2045/0055 , G05D1/0022 , G05D1/0061 , G05D1/0858
Abstract: In some embodiments, a control manager is disposed between the rotor system and the flight control inceptor.The control manager is configured to receive control commands wirelessly from a ground control station, translate the control commands into one or more axes associated with the flight control inceptor, and transmit the translated control commands to the rotor system in place of the instructions received from the pilot via the flight control inceptor.
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公开(公告)号：US20190241251A1
公开(公告)日：2019-08-08
申请号：US15887664
申请日：2018-02-02
Applicant: Bell Helicopter Textron Inc.
Inventor： Brady Garrett Atkins , Robert Paul Reynolds , Carlos Alexander Fenny , Charles Eric Covington
CPC classification number: F16K31/047 , F16K11/20
Abstract: Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body, and multiple motor assemblies coupled to the primary spool that provide selective displacement of the primary spool or the secondary spool. Each motor assembly includes a clutching mechanism that selectively couples a motor of the motor assembly to and from the primary spool.
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315.发明授权公开(公告)号：US10371212B2
公开(公告)日：2019-08-06
申请号：US15375131
申请日：2016-12-11
Applicant: Bell Helicopter Textron, Inc.
Inventor： Ryan Thomas Ehinger
Abstract: A bearing liner allows a bearing to be mounted to a bearing housing even where the coefficients of thermal expansion of the bearing and the housing are different. The bearing liner includes a body portion and a mounting portion. The body portion has a cylindrical substrate that extends about a longitudinal axis of the bearing. The mounting portion includes mounting tabs that extend from the body portion of the liner. The mounting tabs allow the liner to be fixed to the housing and to the bearing. The mounting tabs are configured to flex relative to the body portion of the liner so as to allow for thermal expansion and contraction of the housing relative to the bearing while still securing the bearing to the housing.
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Patent Agency Ranking
公开(公告)号：US20190233079A1
公开(公告)日：2019-08-01
申请号：US15886655
申请日：2018-02-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith
Abstract: An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.
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公开(公告)号：US10352906B2
公开(公告)日：2019-07-16
申请号：US15381021
申请日：2016-12-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert J. Barry , Edward A. Hohman
Abstract: A testing apparatus, inspection system, and method for through-transmission ultrasonic testing. The testing apparatus includes a yoke having a support member with a pair of hinge joints, each hinge joint located on an end of the support member; a pair of arms extending from the support member having a hinge end and a pivotable transducer end, each arm being coupled to the hinge joint at the hinge end and extending to the pivotable transducer end; a pair of transducer support members disposed on each of the pivotal transducer ends; and a tension member connected to the pair of arms for aligning the pair of transducer support members during testing.
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公开(公告)号：US20190211915A1
公开(公告)日：2019-07-11
申请号：US16245498
申请日：2019-01-11
Applicant: Textron Inc.
Inventor： Hunter Davis , Nathan Lundstrom , Logan Bastian , Stephen Deck , Judson Houston , Russell Conine , Deanna Mock , John Stocks , David Horne , Matthew Fields
IPC: F16H57/04 , B62D21/18 , F16H61/662
CPC classification number: F16H57/0489 , B62D21/18 , F16H37/086 , F16H61/0021 , F16H61/662 , F16H2061/0037
Abstract: An off-highway recreational vehicle includes side-by-side passenger and driver seats held within a chassis. The seats sit low in the chassis and are covered by a roll-over protection system (ROPS). The vehicle is powered by an engine rearward of the seats that utilizes a continuously variable transmission (CVT) to provide power to the ground engaging members, wherein the CVT is cooled via air captured by a CVT intake body located adjacent the driver-side seat, between the frame and external panels of the utility vehicle.
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公开(公告)号：US10344846B2
公开(公告)日：2019-07-09
申请号：US15709502
申请日：2017-09-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Scott David Poster
Abstract: A cooling apparatus includes one or more fans and one or more shafts. Each of the one or more fans includes a fan blade assembly. Each of the one or more shafts is operably coupled to an engine or a gearbox that rotates the shaft. Each fan blade assembly of the one or more fans is disposed on one of the shafts.
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公开(公告)号：US20190203795A1
公开(公告)日：2019-07-04
申请号：US16293040
申请日：2019-03-05
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Scott Seifert , Peter Quinn Romano , Thomas Parham
CPC classification number: F16F7/116 , B64C27/001 , B64C29/0033 , F16F15/06
Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.
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