Rotary wing aircraft vibration control system with resonant inertial actuators

A method of operating a vibration control system of a rotary wing aircraft for counteracting vibrations in a vibrating structure of the aircraft comprising:

• monitoring a current and a voltage through a resonant inertial actuator over at least a portion of an interval of time;
• monitoring a vibration frequency of the vibrating structure of the rotary wing aircraft;
• transforming the monitored current and voltage in a time domain in reference to the vibration frequency in quadrature into complex current and voltage values in a frequency domain over at least a portion of the time interval;
• incorporating the complex current and voltage values into a calculation of a value of an operating parameter of the resonant inertial actuator;
• comparing the calculated value of the operating parameter against a threshold relating to a desired range of operation for the resonant inertial actuator;
• and
• limiting a command output of the resonant inertial actuator to maintain the value of the operating parameter within the desired range.