Identification of a linear model of rotor-fuselage dynamics from nonlinear simulation dataLinear regression techniques are used to obtain 9- and 12-degree-of-freedom linear rotorcraft models from the input-output data generated by a nonlinear, blade-element rotorcraft simulation in hover. The resulting models are used to evaluate the coupling of the fuselage modes with the rotor flapping and lead-lag modes at various frequencies. New techniques are proposed and evaluated to improve the identification process, including a method of verifying the assumed model structure by using data sets generated at different input frequencies.
Document ID
19810055721
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Duval, R. W. (NASA Ames Research Center Moffett Field, CA, United States)
Mackie, D. B. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1980
Subject Category
Aircraft Stability And Control
Meeting Information
Meeting: European Rotorcraft and Powered Lift Aircraft Forum