The present work deals with a methodology for the alleviation of loads and corresponding emitted noise generated by blade-vortex interaction (BVI) phenomena occurring on helicopter main rotors in low-speed, descent flight. It consists of a multi-cyclic, optimal control approach\ud
driving higher harmonic blade pitch actuation. First, for the specific flight condition to be examined, the BVI phenomena are simulated as equivalent two-dimensional, multi-vortex, parallel BVI problems and then a local controller methodology is applied for the efficient\ud
identification of the closed-loop control algorithm. In order to assess the capability of the proposed control approach to alleviate rotor blade loads and emitted noise, the results of a numerical investigation concerning a realistic helicopter main rotor in descent flight are\ud
presented and discussed
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.
The aim of this paper is the presentation and application\ud
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\ud
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-\ud
ticularly efficient in that exploits two-dimensional simulations, instead of using three-dimensional, time-consuming predictions.\ud
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
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