Keywords: Active Control with an On-Blade Elevon Control Surface Using Smart Materials and Structures, Analytical Correlation with Experimental Data, Hover and Wind Tunnel Testing of Rotorcraft, Helicopter Rotor Dynamics and Aeroelasticity, Rotor Blade Loads and Vibration Reduction
Abstract: A two-blade, 7.5-ft diameter hingeless rotor model with 10% chord on-blade elevons driven by piezoceramic actuators was tested in hover up to 300 ft/sec tip speed and for advance ratios from 0.1 to 0.3 in forward flight at moderate thrust coefficients and successfully demonstrated cancellation and significant reductions of individual 3, 4, and 5/rev blade vibratory flap bending moments. Aeroelastic and structural dynamic response characteristics were evaluated for a wide range of rotor speed and advance ratio using frequency sweep elevon excitation. Simplified and comprehensive analytical models are used to help understand dynamic response including elevon reversal, elevon effectiveness, bending-torsion interaction, and torsion stiffness effects. The comprehensive analysis successfully reproduced the principal characteristics of the experimental results.
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