Demonstration of Active Vibration Control System on a Korean Utility Helicopter

  • Do-Hyung Kim
  • Dong-Il Kwak
  • Qi Song
Original Paper


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.


Active vibration control system (AVCS) Korean Utility Helicopter (KUH) Circular force generator (CFG) Optimization 



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.


  1. 1.
    Loewy RG (1984) Helicopter vibrations: a technological perspective. J Am Helicopter Soc 29(4):4–30CrossRefGoogle Scholar
  2. 2.
    Reichert G (1980) Helicopter vibration control—a survey. In: 6th European rotorcraft and powered lift aircraft forum, Bristol, England, Sep 16–19, 1980Google Scholar
  3. 3.
    Yun CY, Kim DH, Kang HJ (2013) Vibration prediction of helicopter airframe. In: 2013 KSNVE annual spring conference, Yeosu, April 25–26, 2013Google Scholar
  4. 4.
    Jung SU, Kwak DI, Kim SH, Choi J, Shim DS (2013) Vibration reduction devices for korean utility helicopter. J Korean Soc Aeronaut Sp Sci 41(12):987–993Google Scholar
  5. 5.
    Splettstoesser WR, Heller H, Mercker E, Preisser JS, Yu YH (1995) The HART programme, a quadrilateral cooperative research effort. In: 51st AHS annual forum, Fort Worth, Texas, May 9–11, 1995Google Scholar
  6. 6.
    Milgram J, Chopra I, Straub F (1998) Rotors with trailing edge flaps: analysis and comparison with experimental data. J Am Helicopter Soc 43(4):319–332CrossRefGoogle Scholar
  7. 7.
    Lim JW, Boyd DD Jr., Hoffmann F, van der Wall BG, Kim DH, Jung SN, You YH, Tanabe Y, Bailly J, Lienard C, Delriuex Y (2014) Aeromechanical evaluation of smart- twisting active rotor. In: 40th European rotorcraft forum, Southampton, U.K., Sep 2–5, 2014Google Scholar
  8. 8.
    Kim DH, Kang HJ, Wie SY, Kim SH (2013) Modeling of a rotor system incorporating active tab and analysis of BVI noise reduction characteristics. J Korean Soc Aeronaut Sp Sci 41(11):855–864Google Scholar
  9. 9.
    Staple AE (1990) An evaluation of active control of structural response as a means of reducing helicopter vibration. In: 46th AHS annual forum, vol 1, Washington, D.C., May 21–23, 1990, pp 3–17Google Scholar
  10. 10.
    Welsh W, Fredrickson C, Rauch C, Lyndon I (1995) Flight test of an active vibration control system on the UH-60 Black Hawk helicopter. In: 51st AHS annual forum, Fort Worth, Texas, May 9–11, 1995Google Scholar
  11. 11.
    Millott T, Goodman R, Wong J, Welsh W, Correia J, Cassil C (2003) Risk reduction flight test of a pre-production active vibration control system for the UH-60M. In: 59th AHS annual forum, Phoenix, Arizona, May 6–8, 2003Google Scholar
  12. 12.
    Heilmann J, Swanson D, Badre-Alam A, Narayana Rao KS (2003) Vibration attenuation through the use of active Frahms. In: 59th AHS annual forum, Phoenix, Arizona, May 6–8, 2003Google Scholar
  13. 13.
    Vignal B, Kryzinski T (2005) Development and qualification of active vibration control system for the EC225/EC725. In: 61st AHS annual forum, Grapevine, Texas, June 1–3, 2005Google Scholar
  14. 14.
    Konstanzer P, Enenkl B, Aubourg PA, Cranga P (2008) Recent advances in Eurocopter’s passive and active vibration control. In: 64th AHS annual forum, Montreal, Canada, April 29–May 1, 2008Google Scholar
  15. 15.
    Hoffmann F, Konstanzer P, Priems M, Chemin J (2009) Active cabin vibration reduction for jet-smooth helicopter ride. In: 35th European rotorcraft forum, Hamburg, Germany, September 22–25, 2009Google Scholar
  16. 16.
    Priems M, Kerdreux B, Dreher S, Jouve J, Marrot F, Reymond M (2012) Vibration comfort improvement through active vibration control and its certification on EC130T2. In: 38th European rotorcraft forum, Amsterdam, Netherlands, Sep 4–7Google Scholar
  17. 17.
    Mahmood R, Heverly D II (2012) In-flight demonstration of active vibration control technologies on the bell 429 helicopter. In: 68th AHS annual forum, Fort Worth, Texas, May 1–3Google Scholar
  18. 18.
    Andrews J, Welsh W, Altieri R, DiOttavio J (2014) Ground and flight testing of a hub mounted vibration suppression system. In: 70th AHS annual forum, Montreal, Quebec, Canada, May 20–22, 2014Google Scholar
  19. 19.
    Swanson D, Black P, Girondin V, Bachmeyer P, Jolly M (2015) Active vibration control using circular force generator. In: 41st European rotorcraft forum, Munich, GermanyGoogle Scholar
  20. 20.
    Elliott SJ, Nelson PA (1993) Active noise control. In: IEEE signal processing magazine, pp 12–35CrossRefGoogle Scholar
  21. 21.
    DJolly MR, Rossetti DJ, Southward SC (1995) On actuator weighting in adaptive control systems. In: DSC-Vol. 57-2, IMECE proceedings of the ASME dynamic systems and control division, ASME 1995, pp 843–852Google Scholar
  22. 22.
    Jolly MR, Rossetti DJ, Southward SC (1994) Actuator redundancy in adaptive control systems. In: DE-vol. 75, active control of vibration and noise, ASME 1994, pp 19–24Google Scholar

Copyright information

© The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  1. 1.Aircraft System DivisionKorea Aerospace Research InstituteDaejeonRepublic of Korea
  2. 2.Rotary-Wing Flight Performance TeamKorea Aerospace IndustriesSacheonRepublic of Korea
  3. 3.Electromechanical TechnologyLORD CorporationCaryUSA

Personalised recommendations