Method and system for controlling helicopter vibrations

Details Method and system for controlling helicopter vibrations Method and system for controlling helicopter vibrations

2008-05-13

2008-05-13

Collins, Timothy D. (Department: 3643)

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

C381S071100, C180S312000

Reexamination Certificate

active

07370829

ABSTRACT:
A method/system for controlling helicopter vibrations is provided that includes a vibration canceling force generator for actively generating a vibration canceling force. The system includes a resonant actuator having a natural resonant frequency and a resonant actuator electronic control system. The resonant actuator electronic control system provides an electrical drive current to the resonant actuator to drive the resonant actuator about the resonant frequency when commanded by a received command signal. The resonant actuator has a feedback output with the feedback output fed back into the resonant actuator electronic control system wherein the resonant actuator electronic control system adjusts the electrical drive current based on the resonant actuator feedback output to generate the vibration canceling force.

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