This paper presents the results of an analytical study aimed at predicting the aeromechanical stability of a helicopter in ground resonance, with the inclusion of aerodynamic forces. The theoretical results are found to be in good agreement with the experimental results, available in the literature, indicating that the coupled rotor/fuselage system can be represented by a reasonably simple mathematical model. © 1985 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

C. Venkatesan

Department of Mechanical Engineering

IIT Jodhpur

P.P. Friedmann

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Journal	Journal of Aircraft
ISSN	00218669