公开(公告)号：US11719301B2

公开(公告)日：2023-08-08

申请号：US16399458

申请日：2019-04-30

Applicant: BELL TEXTRON INC.

Inventor： Peter Quinn Romano ,  Michael S. Seifert ,  Jeffrey M. Bosworth

IPC: F16F7/10 ,  B64C17/00

CPC classification number: F16F7/1034 ,  B64C17/00 ,  F16F7/10 ,  F16F7/1017 ,  F16F2222/08 ,  F16F2228/066 ,  F16F2230/18 ,  F16F2236/08

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.

公开(公告)号：US20220144416A1

公开(公告)日：2022-05-12

申请号：US17092296

申请日：2020-11-08

Applicant: Bell Textron Inc.

Inventor： Peter Quinn Romano

IPC: B64C27/00 ,  F16F15/027 ,  F16F7/10

Abstract: A liquid inertia vibration elimination (“LIVE”) system for a rotor system having n number of blades. The LIVE system includes a first tuned vibration reduction component configured to provide a maximum vibratory isolation at a frequency below 2*n/rev and a second tuned vibration reduction component configured to provide a maximum vibratory isolation at a frequency above 3*n/rev.

公开(公告)号：US20210094678A1

公开(公告)日：2021-04-01

申请号：US16584448

申请日：2019-09-26

Applicant: Bell Textron Inc.

Inventor： Peter Quinn Romano ,  Jedediah Bryce Goodell ,  Joshua Andrew Emrich ,  Michael S. Seifert

IPC: B64C27/12 ,  B64C27/00

Abstract: In an embodiment, a rotorcraft includes an airframe; a main rotor transmission; one or more brackets mounting the main rotor transmission to the airframe, longitudinal axes of the one or more brackets being substantially parallel with a longitudinal axis of the rotorcraft; and one or more restraints mounting the main rotor transmission to the airframe, the one or more restraints being mounted at an angle non-orthogonal to the longitudinal axis of the rotorcraft and a lateral axis of the rotorcraft.