Active Twist Rotor Controller Identification for Blade-Vortex Interaction Noise Alleviation

2013 ◽  
Author(s):  
Alessandro Anobile ◽  
Giovanni Bernardini ◽  
M. Gennaretti
Keyword(s):  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Active Twist

Blade-vortex interaction noise reduction with active twist smart rotor technology

2001 ◽  
Vol 10 (1) ◽  
pp. 77-85 ◽  
Author(s):  
Peter C Chen ◽  
James D Baeder ◽  
Robert A D Evans ◽  
John Niemczuk
Keyword(s):  
Noise Reduction ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Active Twist

Active twist smart rotor technology for blade-vortex interaction noise reduction

1999 ◽  
Author(s):  
Peter C. Chen ◽  
James D. Baeder ◽  
Robert A. D. Evans ◽  
John B. Niemczuk ◽  
Paul A. Ross
Keyword(s):  
Noise Reduction ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Active Twist

Synthesis of Active Twist Controller for Rotor Blade–Vortex Interaction Noise Alleviation

2016 ◽  
Vol 53 (6) ◽  
pp. 1865-1874
Author(s):  
Alessandro Anobile ◽  
Giovanni Bernardini ◽  
Massimo Gennaretti ◽  
Claudio Testa
Keyword(s):  
Rotor Blade ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Active Twist

Novel method for calculating two-dimensional blade vortex interaction

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 909-912
Author(s):  
Ronald J. Epstein ◽  
John A. Rule ◽  
Donald B. Bliss
Keyword(s):  
Two Dimensional ◽  
Vortex Interaction ◽  
Blade Vortex Interaction ◽  
Novel Method

Blade-vortex interaction experiments - Velocity and vorticity fields

1990 ◽  
Author(s):  
MICHAEL WILDER ◽  
MATTHEW PESCE ◽  
DEMETRI TELIONIS ◽  
DAVIDR. POLING
Keyword(s):  
Vortex Interaction ◽  
Blade Vortex Interaction

A modified near wake dynamic model for rotor analysis

1999 ◽  
Vol 103 (1021) ◽  
pp. 143-146 ◽  
Author(s):  
T. Wang ◽  
F. N. Coton
Keyword(s):  
High Resolution ◽  
Dynamic Model ◽  
Numerical Evaluation ◽  
Helicopter Rotor ◽  
Vortex Interaction ◽  
Near Wake ◽  
Blade Vortex Interaction ◽  
Wake Model ◽  
Induced Velocity

Abstract The Beddoes near wake model, developed for high resolution blade vortex interaction computations, enables efficient numerical evaluation of the downwash due to trailed vorticity in the near wake of a helicopter rotor. The model is, however, limited by the assumption that the near wake lies in the plane of the rotor and, in some cases, by its inability to accurately evaluate the induced velocity contribution from vorticity trailed from inboard blade sections. In this paper, modifications to the method are proposed which address these issues and allow it to be used with confidence over a wider range of rotor flows.

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