Validation of Comprehensive Helicopter Aeroelastic Analysis with Experimental Data

  • Shrinivas R. Bhat Indian Institute of Science, Bangalore
  • Ranjan Ganguli Indian Institute of Science, Bangalore
Keywords: Helicopter, vibration, validation, aeroelastic analysis, finite element model, rotor blade, aerodynamic models, free-wake models, unsteady aerodynamics, quasi-steady aerodynamics

Abstract

The experimental data for a Cbladed soft-inplane hingeless main rotor is used to validate a comprehensive aeroelastic analysis. A finite element model has been developed for the rotor
blade which predicts rotating frequencies quite well, across a range of rotation speeds. The helicopter is trimmed and the predicted trim-control angles are found to be In the range of
measured values for a variety of flight speeds. Power predictions over a range of forward speeds also compare well. Finally, the aeroelastlc analysis is used to study the Importance of
aerodynamic models on the vibration predict~onU. nsteady aerodynamics and free-wake models have been investigated.
Published
2004-10-01
How to Cite
Bhat, S., & Ganguli, R. (2004). Validation of Comprehensive Helicopter Aeroelastic Analysis with Experimental Data. Defence Science Journal, 54(4), 419-427. https://doi.org/10.14429/dsj.54.2056
Section
Aeronautical Systems