Abstract
The results of this analytical feasibility study suggest that activeblade twist technology is a viable means to reduce blade-vortex interaction(BVI) noise in rotorcraft systems. A linearized unsteady aerodynamics analysiswas formulated and successfully validated with computation fluid dynamics(CFD) analysis. A simple control scheme with three control points was found tobe effective for active BVI noise reduction. Based on current-day actuationtechnology where one to two degrees of twist per blade activation span isexpected, measurable noise reductions of 2-4 dB were predicted for therelatively strong, close vortex interactions. For weaker vortex interactions,reductions of 7-10 dB were predicted. The required twist actuation per bladespan for complete unsteady loading cancellation, however, may be infeasiblebecause of the large stroke and high-frequency activation requirements.
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