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Shock and Vibration
Volume 18, Issue 5, Pages 727-745

Identification of Flap Motion Parameters for Vibration Reduction in Helicopter Rotors with Multiple Active Trailing Edge Flaps

Uğbreve;ur Dalli1 and Şcedilefaatdin Yüksel2

1ASELSAN Inc., MGEO Division, 06511 Akyurt, Ankara, Turkey
2Department of Mechanical Engineering, Faculty of Engineering and Architecture, Gazi University, 06570 Maltepe, Ankara, Turkey

Received 1 October 2009; Revised 21 April 2010

Copyright © 2011 Hindawi Publishing Corporation. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Citations to this Article [3 citations]

The following is the list of published articles that have cited the current article.

  • Devalve, and Pitchumani, “Experimental investigation of the damping enhancement in fiber-reinforced composites with carbon nanotubes,” Carbon, vol. 63, pp. 71–83, 2013. View at Publisher · View at Google Scholar
  • C. DeValve, and R. Pitchumani, “Analysis of vibration damping in a rotating composite beam with embedded carbon nanotubes,” Composite Structures, vol. 110, pp. 289–296, 2014. View at Publisher · View at Google Scholar
  • Shi-Ming Liu, Wei-Dong Yang, Zhi-Hao Yu, and Jie Wu, “Vibratory loads prediction of rotor with trailing edge flaps,” Hangkong Dongli Xuebao/Journal of Aerospace Power, vol. 31, no. 6, pp. 1496–1503, 2016. View at Publisher · View at Google Scholar