Patent ID: 8731743

Claim:
An aircraft, comprising: a non-vibrating structure; a vibrating structure exerting vibratory forces on the non-vibrating structure; and a vibration isolation system, having: an adjustable vibration isolator securely attached to both the non-vibrating structure and the vibrating structure, the vibration isolator being configured to isolate the vibratory forces exerted on the non-vibrating structure; a driver operably associated with the vibration isolator, the driver being configured to selectively adjust the vibration isolator; a sensor system, having: a first sensor associated with the vibration isolator; and a second sensor associated with the vibrating structure; and a control unit in data communication with both the sensor system and the driver, the control unit being configured to analyze a first output signal from the first sensor and a second output signal from the second sensor and configured to command the driver to adjust the vibration isolator; wherein the control unit comprises an algorithm, having: an analog multiplier; and a dynamic detector; wherein the first output signal and the second output signal are multiplied together within the analog multiplier, then passed through the dynamic detector for determining the relative phase angle between the first signal and the second signal; wherein the algorithm determines whether the relative phase angle is equal to 90 degrees, and if so, then the vibration isolator is not adjusted, else, the control unit commands the driver to adjust the vibration isolator; wherein the vibration isolation system continuously monitors the vibratory forces and adjusts the vibration isolator accordingly.