Pressure feedback-based blade–vortex interaction noise controller for helicopter rotors
| Autor: | Giovanni Bernardini, Giorgio Graziani, Massimo Gennaretti, Sara Modini |
|---|---|
| Přispěvatelé: | Modini, S., Graziani, G., Bernardini, G., Gennaretti, M. |
| Rok vydání: | 2018 |
| Předmět: |
020301 aerospace & aeronautics
Acoustics and Ultrasonics Blade (geometry) Rotor aerodynamics blade–vortex interaction loads Computer science Acoustics blade–vortex interaction noise multi-cyclic control rotor aeroacoustics rotor aerodynamics aerospace engineering acoustics and ultrasonics Aerospace Engineering Pressure feedback 02 engineering and technology 01 natural sciences Noise annoyance 010305 fluids & plasmas Vortex Physics::Fluid Dynamics Noise 0203 mechanical engineering Control theory 0103 physical sciences |
| Zdroj: | International Journal of Aeroacoustics. 17:295-318 |
| ISSN: | 2048-4003 1475-472X |
| DOI: | 10.1177/1475472x18774052 |
| Popis: | With the aim of alleviating the noise annoyance emitted by blade–vortex interactions occurring on helicopter main rotors, the present work presents a methodology suitable for the identification of a multi-cyclic harmonic controller based on the actuation of rotor blades equipped with Miniature Trailing Edge Effectors. The objective of the control methodology is the direct suppression of the aerodynamic noise sources by generation of localized high-harmonic blade–vortex interaction counter-actions. The set-up of control devices is selected on the basis of the blade–vortex interaction scenario, taking into account a trade-off between effectiveness and power requirement. The control law is efficiently identified by means of an optimal controller synthesized through suitable two-dimensional multi-vortex, parallel blade–vortex interaction problems. The proposed methodology is validated by the application to realistic helicopter main rotors during low-speed descent flights, numerically simulated through high-fidelity aerodynamic and aeroacoustic solvers based, respectively, upon a three-dimensional free-wake boundary element method to solve the potential flow around rotors in blade–vortex interaction conditions and the Farassat 1A formulation. Results concerning the capability of the proposed controller to alleviate the blade–vortex interaction noise emitted by a realistic helicopter main rotor are presented and discussed. |
| Databáze: | OpenAIRE |
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