Design and Evaluation of a State‐Feedback Vibration Controller
Abstract: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.
Document Type: Research Article
Affiliations: Advanced Rotorcraft Technology, Inc., Los Altos, California
Publication date: July 1, 1984
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