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 |
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.
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