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公开(公告)号：US10232936B2
公开(公告)日：2019-03-19
申请号：US15359305
申请日：2016-11-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Seifert , Peter Quinn Romano , Thomas Parham
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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公开(公告)号：US20200255133A1
公开(公告)日：2020-08-13
申请号：US16272091
申请日：2019-02-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Timothy Kent LEDBETTER , Thomas Parham , Dalton T. Hampton , Frank Stamps , Zachary Edwin Dailey , Robert L. Milliken
Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.
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Patent Agency Ranking
公开(公告)号：US10800518B2
公开(公告)日：2020-10-13
申请号：US16272091
申请日：2019-02-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Timothy Kent Ledbetter , Thomas Parham , Dalton T. Hampton , Frank Stamps , Zachary Edwin Dailey , Robert L. Milliken
Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.
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公开(公告)号：US20180141645A1
公开(公告)日：2018-05-24
申请号：US15359305
申请日：2016-11-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Seifert , Peter Quinn Romano , Thomas Parham
CPC classification number: B64C27/001 , B64C27/04 , B64C29/0033 , B64C2027/005 , F16F7/104 , F16F7/108 , F16F7/116 , F16F7/14 , F16F15/02 , F16F2222/08 , F16F2224/00 , F16F2230/00
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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公开(公告)号：US10386858B2
公开(公告)日：2019-08-20
申请号：US15594393
申请日：2017-05-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Mike Bothwell , Jillian Samantha Alfred , Sung Kyun Kim , Marko Vuga , Matthew Hendricks , Mark Wasikowski , Thomas Parham , Michael Reaugh Smith
Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft.
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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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公开(公告)号：US20180329430A1
公开(公告)日：2018-11-15
申请号：US15594393
申请日：2017-05-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Mike Bothwell , Jillian Samantha Alfred , Sung Kyun Kim , Marko Vuga , Matthew Hendricks , Mark Wasikowski , Thomas Parham , Michael Reaugh Smith
CPC classification number: G05D1/0858 , B64C27/001 , B64C27/04 , B64C27/57 , B64C27/82 , G05D1/0825
Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes receiving a measured yaw rate from a yaw rate sensor or a measured lateral acceleration from a lateral acceleration sensor of the rotorcraft, filtering the measured yaw rate or the measured lateral acceleration using a filter to form a filtered measured yaw rate or a filtered measured lateral acceleration, and regulating a yaw rate or a lateral acceleration of the rotorcraft based on the measured yaw rate or the measured lateral acceleration. The filter includes a bandpass characteristic or a notch characteristic, and the filtering is configured to reduce lateral vibrations caused by airflow in a tail section of the rotorcraft
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