Method and system for controlling helicopter vibrations
First Claim
1. An aircraft vibration canceling force generator for actively generating an aircraft vibration canceling force, said aircraft vibration canceling force generator comprising:
- an aircraft resonant actuator, said resonant actuator including an electromagnetically driven sprung mass, said resonant actuator having a resonant frequency, and a resonant actuator electronic control system having an input for receiving a signal, said resonant actuator electronic control system providing an electrical drive current to said resonant actuator to drive said resonant actuator about said resonant frequency when commanded by a received signal, said resonant actuator having a direct feedback electrical output, said direct feedback electrical output directly fed back into said resonant actuator electronic control system wherein said resonant actuator electronic control system adjusts said electrical drive current based on said resonant actuator direct feedback electrical output to generate said aircraft vibration canceling force.
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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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Citations
41 Claims
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1. An aircraft vibration canceling force generator for actively generating an aircraft vibration canceling force, said aircraft vibration canceling force generator comprising:
an aircraft resonant actuator, said resonant actuator including an electromagnetically driven sprung mass, said resonant actuator having a resonant frequency, and a resonant actuator electronic control system having an input for receiving a signal, said resonant actuator electronic control system providing an electrical drive current to said resonant actuator to drive said resonant actuator about said resonant frequency when commanded by a received signal, said resonant actuator having a direct feedback electrical output, said direct feedback electrical output directly fed back into said resonant actuator electronic control system wherein said resonant actuator electronic control system adjusts said electrical drive current based on said resonant actuator direct feedback electrical output to generate said aircraft vibration canceling force. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A method of making an aircraft vibration canceling force generator, said method comprising the steps of:
- providing an aircraft resonant actuator having a resonant frequency and an electrical output, providing a resonant actuator electronic control system having an input for receiving a signal, said electronic control system providing an electrical drive current to drive said resonant actuator, connecting said resonant actuator with said resonant actuator electronic control system wherein said resonant actuator electronic control system electrical drive current drives said resonant actuator about said resonant frequency when commanded by a received signal, with said resonant actuator feeding said electrical output back into said resonant actuator electronic control system wherein said resonant actuator electronic control system adjusts said electrical drive current based on said resonant actuator electrical output.
- View Dependent Claims (14, 15, 16, 17, 18, 19, 20)
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21. A method of controlling aircraft vibrations, said method comprising the steps of:
- providing a resonant actuator, said resonant actuator including an electromagnetically driven sprung mass, said resonant actuator having a resonant frequency and an electrical output, providing an electronic control system for providing an electrical drive current to drive said resonant actuator, connecting said resonant actuator with said electronic control system, electromagnetically driving said resonant actuator about said resonant frequency with said resonant actuator feeding said electrical output back into said electronic control system and adjusting said electrical drive current based on said resonant actuator electrical output.
- View Dependent Claims (22, 23, 24, 25, 26, 27, 28, 29)
- 30. A helicopter, said helicopter having helicopter vibrations, said helicopter including a helicopter vibration canceling system, said vibration canceling system comprising at least one resonant actuator, said resonant actuator including an electromagnetically driven sprung mass, said resonant actuator having a resonant frequency, and a resonant actuator electronic controller, said resonant actuator electronic controller providing an electrical drive current to said resonant actuator to electromagnetically drive said resonant actuator about said resonant frequency, said resonant actuator having a feedback electrical output, said feedback electrical output fed back into said resonant actuator electronic controller wherein said resonant actuator electronic controller adjusts said electrical drive current based on said resonant actuator feedback electrical output with said helicopter vibration canceling system controlling said helicopter vibrations.
Specification