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.

C. Venkatesan

Department of Mechanical Engineering

IIT Jodhpur

K.A. Yuan

P.P. Friedmann

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Journal	American Society of Mechanical Engineers, Aerospace Division (Publication) AD
Publisher	Publ by ASME, New York, NY, United States
ISSN	07334230