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http://dx.doi.org/10.5139/JKSAS.2009.37.2.139

Vibration Reduction of Composite Helicopter Blades using Active Twist Control Concept  

Pawar, Prashant M. (건국대학교 항공우주정보시스템공학과 대학원)
You, Young-Hyun (건국대학교 항공우주정보시스템공학과 대학원)
Jung, Sung-Nam (건국대학교 항공우주정보시스템공학과)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.37, no.2, 2009 , pp. 139-146 More about this Journal
Abstract
In this study, an assessment is made for the helicopter vibration reduction of composite rotor blades using an active twist control concept. The piezoceramic shear actuation mechanism along with elastic couplings of composite blades is used for vibration reduction. The rotor blades are modeled as composite box-beams with actuator layers bonded on the outer surfaces of the thin-walled section. The governing equations of motion for helicopter blades are obtained using Hamilton's principle. A time domain unsteady aerodynamic theory with free wake model is used to obtain the airloads. Various rotor configurations with different elastic couplings with appropriate actuator placement are used to investigate the hub vibration characteristics. Numerical results show that a substantial reduction of $N_b$/rev hub vibration can be achieved using the optimal control algorithm.
Keywords
Active twist control; Piezoceramic actuator; Vibration reduction; Shear actuator;
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Times Cited By KSCI : 1  (Citation Analysis)
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