Aeroelastic stability of periodic systems with application to rotor blade flutterThe dynamics of a helicopter blade in forward flight are described by a system of linear differential equations with periodic coefficients. The stability of this periodic aeroelastic system is determined, using multivariable Floquet-Liapunov theory. The transition matrix at the end of the period is evaluated by: (1) direct numerical integration, and (2) a new, approximate method, which consists in approximating a periodic function by a series of step functions. The numerical accuracy and efficiency of the methods is compared, and the second method is shown to be superior by far. Results illustrating the effect of the periodic coefficients and various blade parameters are presented.
Document ID
19740043963
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Friedmann, P.
Silverthorn, L. J. (California, University Los Angeles, Calif., United States)
Date Acquired
August 7, 2013
Publication Date
April 1, 1974
Subject Category
Aircraft
Report/Patent Number
AIAA PAPER 74-417
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference