A refined and efficient approach for dynamic analysis of helicopter blades

Research output: Chapter in Book/Report/Conference proceedingConference contribution


This study presents an application of a three-dimensional approach for detailed analysis of an articulated rotor blade undergoing large displacement and elastic deformations. The articulated blade has the geometry, structural and mass properties similar to the UH60 blade. In analyzing an articulated blade, each member of the cross-section is modeled individually. The titanium box-beam and the Graphite-Epoxy skin are modeled using plate elements, the homogeneous core is modeled using solid elements. Lumped mass is used to represent the balance weight. One dimensional spring and damper are also utilized to model the pitch link and the lead-lag damper. A quasi-steady aerodynamic model based on the lifting line theory has been utilized to compute the aerodynamic load. A wind tunnel trim analysis has been utilized to compute the control setting that are required to produce a specific thrust and eliminate the 1/rev flapping motion.

Original languageEnglish (US)
Title of host publication17th AIAA/ASME/AHS Adaptive Structures Conf., 11th AIAA Non-Deterministic Approaches Conf., 10th AIAA Gossamer Spacecraft Forum, 5th AIAA Multidisciplinary Design Optimization Specialist Conf., MDO
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781563479731
StatePublished - 2009

Publication series

NameCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
ISSN (Print)0273-4508

ASJC Scopus subject areas

  • Architecture
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering


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