Fluidic flexible matrix composite (FFMC) tube vibration control system

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.