US 11,719,301 B2
Fluidic flexible matrix composite (FFMC) tube vibration control system
Peter Quinn Romano, Fort Worth, TX (US); Michael S. Seifert, Southlake, TX (US); and Jeffrey M. Bosworth, Argyle, TX (US)
Assigned to TEXTRON INNOVATIONS INC., Providence, RI (US)
Filed by BELL TEXTRON INC., Fort Worth, TX (US)
Filed on Apr. 30, 2019, as Appl. No. 16/399,458.
Prior Publication US 2020/0347903 A1, Nov. 5, 2020
Int. Cl. F16F 7/10 (2006.01); B64C 17/00 (2006.01)
CPC F16F 7/1034 (2013.01) [B64C 17/00 (2013.01); F16F 7/10 (2013.01); F16F 7/1017 (2013.01); F16F 2222/08 (2013.01); F16F 2228/066 (2013.01); F16F 2230/18 (2013.01); F16F 2236/08 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An aircraft comprising:
an aircraft component;
a sensor operable to detect a frequency of a vibration of the aircraft component;
a multiple frequency vibration absorber coupled to the aircraft component and configured to absorb the vibration, the multiple frequency vibration absorber comprising:
a beam element attached to the aircraft component;
a fluidic flexible matrix composite (FFMC) tube coupled to the beam element, wherein the FFMC tube is configured to absorb the vibration based on a stiffness of the FFMC tube;
a valve fluidically coupled to the FFMC tube, wherein the valve is to control the stiffness of the FFMC tube based on regulating a flow of a liquid through the FFMC tube; and
a controller to actively control absorption of the vibration via the FFMC tube based on actuating the valve, wherein the controller is configured to:
open the valve to decrease the stiffness of the FFMC tube based on the sensor detecting that the vibration is in a first frequency range, and
close the valve to increase the stiffness of the FFMC tube based on the sensor detecting that the vibration is in a second frequency range.