The present work focuses on the alleviation of Blade Vortex Interaction (BVI) noise annoyance through a control methodology generating high-frequency aerodynamic BVI counter-actions. The low-power requirements make the Micro-Trailing Edge Effectors (MiTEs) particularly suited for this kind of application. The controller layout is set by observing the BVI scenario while the actuation law is efficiently synthesized through a process based on an analytical unsteady sectional aerodynamic formulation. The validation of the proposed control methodology is carried out through numerical investigations of a realistic helicopter main rotor in flight descent, obtained using computational tools for potential-flow aerodynamic and aeroacoustic analyses based on boundary element method solutions. In order to capture the aerodynamic influence of MiTEs through potential-flow simulations, the MiTEs are replaced by trailing edge plain flaps which provide equivalent aerodynamic responses. Results concerning the proposed controller capability to alleviate high-frequency blade loads and subsequent emitted noise from BVI events are presented and discussed.

Modini, S., Graziani, G., Bernardini, G., Gennaretti, M. (2018). Blade-Vortex Interaction Noise Controller Based on Miniature Trailing Edge Effectors. INTERNATIONAL JOURNAL OF ACOUSTICS AND VIBRATION, 23(3), 378-384 [10.20855/ijav.2018.23.31313].

Blade-Vortex Interaction Noise Controller Based on Miniature Trailing Edge Effectors

Bernardini G.;Gennaretti M.
2018

Abstract

The present work focuses on the alleviation of Blade Vortex Interaction (BVI) noise annoyance through a control methodology generating high-frequency aerodynamic BVI counter-actions. The low-power requirements make the Micro-Trailing Edge Effectors (MiTEs) particularly suited for this kind of application. The controller layout is set by observing the BVI scenario while the actuation law is efficiently synthesized through a process based on an analytical unsteady sectional aerodynamic formulation. The validation of the proposed control methodology is carried out through numerical investigations of a realistic helicopter main rotor in flight descent, obtained using computational tools for potential-flow aerodynamic and aeroacoustic analyses based on boundary element method solutions. In order to capture the aerodynamic influence of MiTEs through potential-flow simulations, the MiTEs are replaced by trailing edge plain flaps which provide equivalent aerodynamic responses. Results concerning the proposed controller capability to alleviate high-frequency blade loads and subsequent emitted noise from BVI events are presented and discussed.
Modini, S., Graziani, G., Bernardini, G., Gennaretti, M. (2018). Blade-Vortex Interaction Noise Controller Based on Miniature Trailing Edge Effectors. INTERNATIONAL JOURNAL OF ACOUSTICS AND VIBRATION, 23(3), 378-384 [10.20855/ijav.2018.23.31313].
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11590/340526
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