Bhat, Shrinivas R and Ganguli, Ranjan (2004) Validation of Comprehensive Helicopter Aeroelastic Analysis with Experimental Data. In: Defence Science Journal, 54 (4). pp. 419-427.
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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.
|Item Type:||Journal Article|
|Additional Information:||The copyright for this article belongs to Defence Scientific Information Documentation Centre.|
|Keywords:||Helicopter;vibration;validation;aeroelastic analysis;finite element model;rotor blade;aerodynamic models;free-wake models;unsteady aerodynamics;quasi-steady|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||15 Apr 2005|
|Last Modified:||20 Jan 2012 09:21|
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