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Demonstration of Active Vibration Control System on a Korean Utility Helicopter

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Abstract

Technology demonstration program was performed between June 2013 and January 2014 in Sacheon Korea to validate the performance of LORD Corporation (LORD)-designed active vibration control system (AVCS) on Korean Utility Helicopter platform. Optimal configuration of actuators was investigated by numerical calculation using ground and flight test data, and its performance was evaluated through the flight tests. 14 control accelerometers were used for vibration-level measurement and optimal configuration of 2–6 circular force generator test groups was investigated. Although the predicted vibration levels of aircraft showed better performance with increasing number of actuators, the weight and cost trade-off should be considered during the design. Flight tests showed that the vibration levels with AVCS at the cockpit area and the cabin area were reduced more than that of the tuned vibration absorber (TVA). Moreover, it was possible to configure AVCS with lower weight than the TVA.

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Acknowledgements

This study was supported by the LCH Core Technology Development Program (Project number: 10053157) funded by the Ministry of Trade, Industry and Energy, Republic of Korea.

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Authors and Affiliations

  1. Aircraft System Division, Korea Aerospace Research Institute, Daejeon, 34133, Republic of Korea

    Do-Hyung Kim

  2. Rotary-Wing Flight Performance Team, Korea Aerospace Industries, Sacheon, 52529, Republic of Korea

    Dong-Il Kwak

  3. Electromechanical Technology, LORD Corporation, Cary, NC, 27511-7923, USA

    Qi Song

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  1. Do-Hyung Kim
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  2. Dong-Il Kwak
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  3. Qi Song
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Correspondence to Do-Hyung Kim.

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Kim, DH., Kwak, DI. & Song, Q. Demonstration of Active Vibration Control System on a Korean Utility Helicopter. Int. J. Aeronaut. Space Sci. 20, 249–259 (2019). https://doi.org/10.1007/s42405-018-0106-3

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  • DOI: https://doi.org/10.1007/s42405-018-0106-3

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