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Design and Evaluation of a State‐Feedback Vibration Controller

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A new approach to active control of rotorcraft vibrations involves using feedback of fuselage accelerations through undamped oscillators, tuned to the frequency at which vibration is to be suppressed. This paper presents a simplified formulation of the algorithm and investigates implementation considerations such as sampled‐data effects and actuator dynamics. Digital compensation for these effects is designed, and the resulting controller is evaluated on a computer simulation of the Rotor Systems Research Aircraft for a wide range of flight conditions.
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Document Type: Research Article

Affiliations: Advanced Rotorcraft Technology, Inc., Los Altos, California

Publication date: 1984-07-01

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  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

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