The equations of motion for the coupled rotor/isolator/fuselage dynamical system are formulated for the prediction of vibrations in helicopters during forward flight. Using a combined Floquet theory/frequency-response technique, the equations are solved to predict the vibratory loads at the various locations of the helicopter. In addition, the influence of the isolator on the hub and blade loads is established. © 1989 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

C. Venkatesan

Department of Mechanical Engineering

IIT Jodhpur

R. Sivaramakrishnan

T.K. Varadan

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Journal	Journal of Aircraft
ISSN	00218669