This paper describes an aeroelastic simulation of a fully elastic hingeless helicopter rotor incorporating a partial span trailing edge flap. Aerodynamic loads are provided by a new, two-dimensional, compressible flow unsteady aerodynamic model developed for an airfoil/flap combination and unsteady freestream. Aerodynamic loads are approximated in the frequency domain as rational functions of the Laplace variable using a least squares fit to oscillatory response data. Transformation to the time domain yields a state space model for the unsteady aerodynamic loads. Frequency domain loads are obtained using a two dimensional doublet-lattice analysis. Vibration control studies using the actively controlled flap are presented, with comparisons to results obtained using quasisteady aerodynamics.
Application of a new compressible time domain aerodynamic model to vibration reduction in helicopters using an actively controlled flap
Anwendung eines neuen zeitabhängigen aerodynamischen Modells zur Schwingungsreduktion von Hubschrauberrotorblättern unter Berücksichtigung von aktiv gesteuerten Klappen
Journal of the American Helicopter Society ; 46 , 1 ; 32-43
2001
14 Seiten, 16 Bilder, 6 Tabellen, 36 Quellen
Article (Journal)
English
Hubschrauber , Rotor (Drehflügel) , Aerodynamik , numerische Simulation , elastische Eigenschaft , Spannweite , kompressible Strömung , Rechenmodell , Machzahl , Flugmechanik , Frequenzbereich , Schwingungsdämpfung , Steuerung und Regelung , Laplace-Gleichung , Wechsellast (mechanisch) , Theorie-Experiment-Vergleich
Reduction of Vibrations due to Dynamic Stall in Helicopters using an Actively Controlled Flap
British Library Conference Proceedings | 2002
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