DOI QR코드

DOI QR Code

고조파제어(HHC) 기법을 이용한 저속 하강 비행중인 로터의 진동하중 억제에 관한 연구

Vibratory Loads Reduction of a Rotor in Slow Descent using Higher Harmonic Control Technology

  • You, Younghyun (Department of Aerospace Information Engineering, Konkuk University) ;
  • Jung, Sung Nam (Department of Aerospace Information Engineering, Konkuk University)
  • 투고 : 2013.04.01
  • 심사 : 2013.05.22
  • 발행 : 2013.06.01

초록

본 연구에서는 능동적인 블레이드 제어기법인 고조파제어(Higher Harmonic Control, HHC) 기법을 적용하여 로터의 허브 진동하중을 억제하기 위한 최적 제어입력을 탐색하였다. 통합 공탄성 해석 프로그램인 CAMRAD II를 이용하여 HART II 로터를 모델링하고 다양한 HHC 입력 조건에 대하여 파라미터 연구를 수행하여 최대의 진동하중을 감소시키기 위한 제어입력을 찾고, HART II 시험에서 정한 최소 진동 조건에서의 허브 진동하중과 비교하였다. 파라미터 연구를 통하여 HART II 시험에서의 최소 진동 조건에서는 진동하중이 증가하는 것을 확인하였다. 허브 진동하중을 감소시키기 위한 최적의 제어입력은 3/rev의 가진주파수에서 찾을 수 있었고 0.8도의 진폭과 350도의 위상각을 갖는 제어입력을 이용하는 경우에 기준조건대비 약 45%의 허브 진동하중 감소효과를 얻었다. HHC 기법을 이용하는 경우의 로터의 파워 감소는 5% 미만으로 나타나고, 성능이 향상되는 경우에는 대부분 진동이 증가하는 경향을 보였다.

In this paper, a higher harmonic control (HHC) methodology is applied to find the optimum input scenario for the vibratory hub loads reduction. A comprehensive aeroelastic analysis code, CAMRAD II, is used to model the HART (Higher-harmonic-control Aeroacoustic Rotor Test) II rotor, and parametric study is conducted for the best HHC inputs leading to a minimum vibration (MV) condition. The resulting outcomes are compared with the earlier HART II test results. It is indicated that the control input adopted in the MV condition showed less satisfactory results. The new MV condition obtained in the present investigation can achieve 45% lower vibration level than the baseline uncontrolled condition. The optimum HHC input results lead to 3/rev harmonic input having $0.8^{\circ}$ amplitude and $350^{\circ}$ phase angle. About 5% reduction in the required power is possible but accompanies with the increase of vibration level.

키워드

참고문헌

  1. Amer, K. B., and Neff, J. R., "Vertical Plane Pendulum Absorbers for Minimizing Helicopter Vibratory Loads," Journal of the American Helicopter Society, Vol. 19, No. 4, 1974, pp.44-48. https://doi.org/10.4050/JAHS.19.44
  2. Taylor, R. B., "Helicopter Vibration Reduction by Rotor Blade Modal Shaping," 38th AHS Annual Forum, Anaheim, 1982, pp.99-101.
  3. Welsh, W. A., von Hardenberg, P. C., and Staple, A. E., "Test and Evaluation of Fuselage Vibration Utilizing Active Control of Structural Response(ASCR) Optimized to ADS-27," 46th AHS Annual Forum, Washington DC, 1990, pp.21-37.
  4. Nguyen, K., and Chopra, I., "Application of Higher Harmonic Control to Rotors Operating at High Speed and Thrust," Journal of the American Helicopter Society, Vol. 35, No. 3, 1990, pp.78-89. https://doi.org/10.4050/JAHS.35.78
  5. Jacklin, S. A., Habor, A., de Simone, G., Norman, T. R., Kitaplioglu, C., and Shinoda, P., "Full-Scale Wind Tunnel Test of an Individual Blade Control System for a UH-60 Helicopter," 58th AHS Annual Forum, Montreal, 2002, pp.1103-1114.
  6. Ravichandran, K., Ananthan, S., Chopra, I. and Hein, B., "Active Rotor Controls for Vibration Reduction and Performance Enhancement," AHS Specialists' Conference on Aeromechanics, San Fancisco, CA, 2010.
  7. Matthew, L. W., Paul, H., M., William, T. Y., Jr., Chester, W., L., Carlos, E. S. C., and Shin, S. J., "Vibratory Loads Reduction Testing of the NASA/ARMY/MIT Active Twist Rotor," 57th AHS Annual Forum, Washington DC, 2001.
  8. Payne, P. R., "Higher Harmonic Control," Aircraft Engineering, Vol. 30, 1958, pp.222-226. https://doi.org/10.1108/eb033000
  9. Kessler, Ch., "Active Rotor Control for Helicopters: Motivation and Survey on Higher Harmonic Control," 36th European Rotorcraft Forum, 2010, Paper 045-I.
  10. Lim, J. W., Tung, C., Yu, Y. H., "Prediction of Blade-Vortex Interaction Airloads with Higher-Harmonic Pitch Controls using the 2GCHAS Comprehensive Code," Journal of Pressure Vessel Technology, Vol. 123, 2001, pp.469-474. https://doi.org/10.1115/1.1401025
  11. van der Wall, B. G., "2nd HHC Aeroacoustic Rotor Test(HART II) - Part I: Test Documentation - Institute Report IB 111-2003/31," German Aerospace Center (DLR), Braunschweig, Germany, 2003.
  12. Johnson, W. "CAMRAD II, Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics," Palo Alto, CA, Johnson Aeronautics, 1992.
  13. Splettstoesser, W. R., Schultz, K. J., Kube, R., Brooks, T. F., Booth, E. R., Niesl, G., Streby, O., "A Higher Harmonic Control Test in the DNW to Reduce Impulsive BVI Noise," Journal of the American Helicopter Society, Vol. 39, No. 4, 1994, pp.3-13. https://doi.org/10.4050/JAHS.39.3