AEROELASTIC RESPONSE OF SWEPT TIP ROTORS INCLUDING THE EFFECTS OF BVI

An aeroelastic response simulation capability for Blade Vortex Interaction (BVI) effects on advanced geometry rotors is described. A structural model for composite blades with swept tips has been combined with a free wake model. Correlation studies have been conducted to validate the structural model/wake combination. The effect of BVI on swept tip rotors is studied so as to gain an improved understanding of its physical mechanism. An actively controlled trailing edge flap has been implemented in the model in order to develop an active control strategy for BVI induced vibration alleviation. Results indicate that the actively controlled flap has remarkable potential for reducing the 4/rev vibratory hub loads induced by BVI at low advance ratios (μ = 0.15).