Transactions of the Korean Society for Noise and Vibration Engineering (한국소음진동공학회논문집)

The Korean Society for Noise and Vibration Engineering (한국소음진동공학회)
권호 표지
DOI QR코드

DOI QR Code

Enhancement of SNUF Active Trailing-edge Flap Blade Mechanism Design

SNUF뒷전 플랩 블레이드 메커니즘의 설계 개선

  • Natarajan, Balakumaran (School of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Eun, WonJong (School of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Shin, SangJoon (School of Mechanical and Aerospace Engineering, and Institute of Advanced Aerospace Technology, Seoul National University)
  • Received : 2013.03.14
  • Accepted : 2013.05.22
  • Published : 2013.07.20
Download PDF
⟨ Previous Next ⟩

Abstract

Seoul National University flap(SNUF) blade is a small-scale rotor blade incorporating a small trailing-edge flap control surface driven by piezoelectric actuators at higher harmonics for vibration attenuation. Initially, the blade was designed using two-dimensional cross-section analysis and geometrically exact one-dimensional beam analysis, and its material configuration was finalized. A flap-deflection angle of ${\pm}4^{\circ}$ was established as the criterion for enhanced vibration reduction based on an earlier simulation. The flap-linkage mechanism was designed and static bench tests were conducted for verifying the performance of the flap-actuation mechanism. Different versions of test beds were developed and tested with the designed flap and the selected APA 200M piezoelectric actuators. Through significant improvements, a maximum deflection of ${\pm}3.7^{\circ}$ was achieved. High-frequency experiments were conducted for evaluating the performance, and the transfer function of the test bed was determined experimentally. With the static tests almost complete, the rotor power required for testing the blade in a whirl tower (centrifugal environment) was calculated, and further preparations are underway.

SNUF(Seoul National University flap) 블레이드는 고주파 영역에서 진동 감쇠를 위하여, 압전작동기에 의해 움직이는 뒷전 플랩이 장착되어 있는 축소형 로터 블레이드이다. 이 블레이드를 설계하기 위하여 2차원 단면 해석과 1차원 기하학적 정밀 보 해석이 수행되었고, 사용할 재료의 특성을 확인하였다. 이전 연구자들의 실험을 참조하여, ${\pm}4^{\circ}$의 플랩 변위각을 진동감쇠를 위한 설계요건으로 선정하였다. 플랩의 연결 메커니즘을 설계하고, 설계된 메커니즘의 성능을 확인하기 위하여 정적 벤치 시험을 수행하였다. 개선된 버전의 플랩 장치를 설계하고 시험하였으며, 압전작동기로는 APA 200M을 선정하였다. 장비의 개선을 통하여, 최대 플랩변위가 ${\pm}3.7^{\circ}$에 도달하였다. 성능을 평가하기 위하여 고주파 실험을 수행하였으며, 플랩 장치의 전달 함수를 실험적으로 결정하였다. 정적 시험을 완료하여, 훨타워 시험을 위하여 필요한 로터의 요구마력을 계산하였고, 그 이외의 준비가 진행 중에 있다.

Keywords

References

  1. Johnson, W., 1994, Helicopter Theory, Chap. 12, Dover Publications, Inc., N.Y.
  2. Newman, S., 1994, The Foundations of Helicopter Flight, Chap. 10, E. A., Great Britain.
  3. Roget, B., 2004, Individual Blade Control of Vibration Reduction of a Helicopter with Dissimilar Blades, Ph.D. Thesis, Chap. 1, Dept. of Aerospace Engineering, University of Maryland.
  4. Shin, S. -J., Cesnik, C. E. S. and Hall, S. R., 2007, Design and Simulation of Integral Twist Control for Helicopter Vibration Reduction, International Journal of Control, Automation, and Systems, Vol. 5, No. 1, pp. 24-34.
  5. Wilbur, M. L., Mirick, P. H., Yeager, W. T., Jr., Langston, C. W., Cesnik, C. E. S. and Shin, S. J., 2002, Vibratory Loads Reduction Testing of the NASA/Army/MIT Active Twist Rotor, Journal of the American Helicopter Society, Vol. 47, No. 2, pp. 123-133. https://doi.org/10.4050/JAHS.47.123
  6. Roth, D., Enenkl, B. and Dieterich, O., 2006, Active Rotor Control by Flaps for Vibration Reduction- Full Scale Demonstrator and First Flight Test Results, 32nd European Rotorcraft Forum, The Netherlands.
  7. Konstanzer, P., Enenkl, B., Aubourg, P.-A. and Cranga, P., 2008, Recent Advances in Eurocopter's Passive and Active Vibration Control, 64th AHS Annual Forum, Montreal, Canada.
  8. Straub, F., Anand, V., Birchette, T. and Lau, B., 2009, SMART Rotor Development and Wind-Tunnel Test, 35th European Rotorcraft Forum, Hamburg, Germany.
  9. Kottapalli, S., 2011, Enhanced Correlation of SMART Active Flap Rotor Loads, 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, Colorado.
  10. Mainz, H., van der Wall, B. G., Leconte, P., Ternoy, F. and des Rochettes, H. M., 2005, ABC Rotor Blades: Design, Manufacturing and Testing, 31st European Rotorcraft Forum, Florence, Italy.
  11. Feszty, D., Nitzsche, F., Khomutov, K., Lynch, B. K., Mander, A. and Ulker, F. D., 2008, Design and Instrumentation of the SHARCS Scaled Rotor with Three Independent Control Systems, American Helicopter Society 64th Annual Forum, Montreal, Canada.
  12. Feszty, D. and Nitzsche, F., 2011, Review of Active Rotor Control Research in Canada, Int. Journal of Aeronautical and Space Sciences, Vol. 12, No. 2, pp. 93-114. https://doi.org/10.5139/IJASS.2011.12.2.93
  13. Balakumaran, N., Eun, W.-J., Lee, J.-H. and Shin, S.-J., 2012, Structural Design of an Active Trailing-Edge Flap Blade for Helicopter Vibration Control, Proceedings of the 53rd AIAA/ASME/ASCE/ AHS/ASC Structures, Structural Dynamics and Materials Conference-Adaptive Structures Forum, Honolulu, Hawaii, USA.
  14. http://www.cedrat-technologies.com/(accessed 11/2012)
  15. Koratkar, N. A. and Chopra, I., 2002, Wind Tunnel Testing of a Smart Rotor Model with Trailing-edge Flaps, Journal of the American Helicopter Society, Vol. 47, No. 4, pp. 263-272. https://doi.org/10.4050/JAHS.47.263
  16. Clement, J. W., Brei, D. and Barrett, R., 1999, Wind Tunnel Testing of a High Authority Airspeed Insensitive Rotor Blade Flap, 40th AIAA/ASME/ASCE/ AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit, St. Louis, MO, USA.
  17. Prechtl, E. F., 2000, Design and Imple-mentation of a Piezoelectric Servo-flap Actuation System for Helicopter Rotor Individual Blade Control, Ph.D. Thesis, Chap. 4, Dept. of Aeronautics and Astronautics, MIT.
  18. http://www.mathworks.co.kr/kr/help/signal/ref/ tfestimate.html(accessed 02/2013)
  19. Laxman, V., Lim, J. H., Shin, S. J., Ko, K. H. and Jung, S. N., 2011, Power and Trim Estimation for Helicopter Sizing and Performance Analysis, Int'l Journal of Aeronautical and Space Science, Vol. 12, No. 2, pp. 156-162. https://doi.org/10.5139/IJASS.2011.12.2.156
  20. Koratkar, N. A. and Chopra, I., 1999, Design, Fabrication and Testing of a Mach Scaled Rotor Model with Trailing-Edge Flaps, American Helicopter Society 55th Annual Forum, Montreal, Canada.
  21. http://www.astbearings.com/product.html?product=F2-6 (accessed 11/2012)
  22. Lee, J.-H., Kim, T.-S. and Shin, S.-J., 2009, Design of an Intelligent Rotor with Flap for Vibration Reduction in Helicopters, Proceedings of the KSNVE Annual Spring Conference, pp. 460-461.
  23. Lee, J.-H., Choe, J.-H. and Shin, S.-J., 2011, Development of an Intelligent Active Trailing-edge Flap Rotor to Reduce Vibratory Loads in Helicopter, Proceedings of the KSNVE Annual Spring Conference pp. 492-497.

Cited by

  1. Active Gurney Flap Design Modification for High Speed Operation and Natural Frequency Estimate vol.25, pp.10, 2015, https://doi.org/10.5050/KSNVE.2015.25.10.667