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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：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：US20200347903A1
公开(公告)日：2020-11-05
申请号：US16399458
申请日：2019-04-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Peter Quinn Romano , Michael S. Seifert , Jeffrey M. Bosworth
Abstract: An aircraft comprises an aircraft component, a sensor, and a multiple frequency vibration absorber (absorber). The sensor is operable to detect a frequency of a vibration of the aircraft component. The absorber is coupled to the aircraft component and configured to absorb the vibration. The absorber comprises a beam element, a fluidic flexible matrix composite (FFMC) tube, a valve, and a controller. The beam element is attached to the aircraft component. The fluidic flexible matrix composite (FFMC) tube is coupled to the beam element and is operable to absorb the vibration based on a stiffness of the FFMC tube. The valve is fluidically coupled to the FFMC tube and is to control the stiffness of the FFMC tube based on regulating a flow of a liquid through the FFMC tube. The controller can actively control absorption of the vibration via the FFMC tube based on opening and/or closing the valve.
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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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