The aim of the present work is the presentation and application of a methodology for the identification of multi-cyclic higher harmonic actuation of blade pitch motion suited for the alleviation of BVI loads, and hence of BVI noise annoyance generated by helicopter main rotors in lowspeed descent flight. The blade pitch actuation is defined by a feedback control law obtained through an optimal control approach based on the minimization of a cost function. In particular, first, strong BVI phenomena occurring in the specific flight condition are simulated as equivalent two-dimensional, multi-vortex, parallel BVI problems, and then a local controller methodology is applied for the efficient identification of the closed-loop control algorithm. This control synthesis methodology is validated by application of the identified gain matrices to a realistic helicopter main rotor in descent flight, and preliminary results concerning its capability to alleviate blade loads and emitted noise are presented and discussed.

Blade-Vortex Interaction Control Methodology Based on Two Dimensional Analysis / Modini, Sara; Graziani, Giorgio; Bernardini, G.; Gennaretti, M.. - STAMPA. - (2013), pp. ---. (Intervento presentato al convegno 22nd Italian Association of Aeronautics and Astronautics Conference tenutosi a Napoli, ITA nel 9-12/9/2013).

Blade-Vortex Interaction Control Methodology Based on Two Dimensional Analysis

MODINI, SARA;GRAZIANI, Giorgio;
2013

Abstract

The aim of the present work is the presentation and application of a methodology for the identification of multi-cyclic higher harmonic actuation of blade pitch motion suited for the alleviation of BVI loads, and hence of BVI noise annoyance generated by helicopter main rotors in lowspeed descent flight. The blade pitch actuation is defined by a feedback control law obtained through an optimal control approach based on the minimization of a cost function. In particular, first, strong BVI phenomena occurring in the specific flight condition are simulated as equivalent two-dimensional, multi-vortex, parallel BVI problems, and then a local controller methodology is applied for the efficient identification of the closed-loop control algorithm. This control synthesis methodology is validated by application of the identified gain matrices to a realistic helicopter main rotor in descent flight, and preliminary results concerning its capability to alleviate blade loads and emitted noise are presented and discussed.
2013
22nd Italian Association of Aeronautics and Astronautics Conference
Keywords: flapping wing; boundary element method; nonlinear FEM; aeroelasticity; partitioned coupling.
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Blade-Vortex Interaction Control Methodology Based on Two Dimensional Analysis / Modini, Sara; Graziani, Giorgio; Bernardini, G.; Gennaretti, M.. - STAMPA. - (2013), pp. ---. (Intervento presentato al convegno 22nd Italian Association of Aeronautics and Astronautics Conference tenutosi a Napoli, ITA nel 9-12/9/2013).
File allegati a questo prodotto
Non ci sono file associati a questo prodotto.

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/548239
 Attenzione

Attenzione! I dati visualizzati non sono stati sottoposti a validazione da parte dell'ateneo

Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus ND
  • ???jsp.display-item.citation.isi??? ND
social impact