Abstract
This paper deals with an efficient computational process for the synthesis of a low-frequency controller aimed at alleviating helicopter rotor blade–vortex interaction noise. It is based on an optimal, multicyclic, control approach that exploits distributed torque loads actuated by smart materials to twist rotor blades at the 2/rev frequency (active twist rotor concept). Aeroacoustic rotor simulations are based on aerodynamic and aeroelastic tools capable of accurately predicting wake–blade miss distance, which plays a crucial role in blade–vortex interaction noise emission. Its modification is the main objective of the proposed controller action. The control law is identified through a numerically efficient aeroacoustic solver based on analytical–numerical sectional aerodynamics modeling. Numerical investigations first examine noise emission sensitivity to active twist actuation, then identify control and output variables suitable for the closed-loop controller. Finally effectiveness of the proposed low-frequency feedback control law for blade–vortex interaction noise alleviation is assessed by application to helicopter rotor in descent flight.
Published Version
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