The aim of this paper is the presentation and application of a methodology for the identification of a multi-cyclic, higher harmonic blade pitch actuation controller suited for alleviating impulsive noise induced by Blade-Vortex Interactions (BVI). The blade pitch actuation is driven by a feedback control law derived by an optimal linear-quadratic regulator control formulation based on simulations provided by an equivalent two-dimensional, multi-vortex, parallel BVI problem that describes the aerodynamic response of elastic rotor blade cross sections in BVI conditions. This control law identification process is par- ticularly efficient in that exploits two-dimensional simulations, instead of using three-dimensional, time-consuming predictions. In order to examine the effectiveness of the proposed controller in alleviating BVI noise, it is applied to the analysis of a realistic helicopter main rotor in descent flight.
Modini, S., Graziani, G., Bernardini, G., Gennaretti, M. (2014). Synthesis of a Rotor Noise Controller by Parallel Blade-Vortex Interaction Aeroelastic Modelling. In Proceedings of ASME 2014 Pressure Vessels & Piping Conference, PVP2014 (peer--reviewed paper) [10.1115/PVP2014-28258].
Synthesis of a Rotor Noise Controller by Parallel Blade-Vortex Interaction Aeroelastic Modelling
BERNARDINI, Giovanni;GENNARETTI, MASSIMO
2014-01-01
Abstract
The aim of this paper is the presentation and application of a methodology for the identification of a multi-cyclic, higher harmonic blade pitch actuation controller suited for alleviating impulsive noise induced by Blade-Vortex Interactions (BVI). The blade pitch actuation is driven by a feedback control law derived by an optimal linear-quadratic regulator control formulation based on simulations provided by an equivalent two-dimensional, multi-vortex, parallel BVI problem that describes the aerodynamic response of elastic rotor blade cross sections in BVI conditions. This control law identification process is par- ticularly efficient in that exploits two-dimensional simulations, instead of using three-dimensional, time-consuming predictions. In order to examine the effectiveness of the proposed controller in alleviating BVI noise, it is applied to the analysis of a realistic helicopter main rotor in descent flight.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.