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Structural dynamic model of composite rotor blades undergoing moderate deflections
K.A. Yuan, , P.P. Friedmann
Published in Publ by ASME, New York, NY, United States
Volume: 30
Pages: 127 - 155
This paper presents a concise description of a structural dynamic model for composite rotor blades, with straight and swept tips, undergoing moderate deflections. The model can represent anisotropic totor blades, with arbitrary cross sections and is valid for the moderate amount of built-in twist encountered in helicopter rotor blades. The results illustrate the effects of composite ply orientation and tip sweep on the natural frequencies of composite blades. The paper also presents some interesting observations on the treatment of the axial degree of freedom, which plays an important role in the structural dynamic modeling of composite rotor blades.
About the journal
JournalAmerican Society of Mechanical Engineers, Aerospace Division (Publication) AD
PublisherPubl by ASME, New York, NY, United States