| || Validation of comprehensive helicopter aeroelastic analysis with experimental data
Author : Bhat, Shrinivas R.;Ganguli, Ranjan
Source : Defence Science Journal ; Vol:54(4) ; 2004 ; pp 419-427
Subject : 629.7 Aeronautics;533.6 Aerodynamics
Keywords : Helicopter ;Aeroelastic analysis;Finite element model;Rotor blade;Aerodynamic models;Aerodynamics;Quasi steady aerodynamics;Free wake models
Abstract : The experimental data for a 4-bladed 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 aeroelastic analysis is used to study the importance of aerodynamic models on the vibration prediction. Unsteady aerodynamics and free-wake models have been investigated.