Author： Myrtle Timothy F. Friedmann Peretz P.
Publisher： AHS International
ISSN： 2161-6027
Source： Journal of the American Helicopter Society, Vol.46, Iss.1, 2001-01, pp. : 32-43
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Abstract
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, vith comparisons to results obtained using quasisteady aerodynamics.
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