A Perturbation Solution of Rotor Flapping Stability
ARMY AIR MOBILITY RESEARCH AND DEVELOPMENT LAB MOFFETT FIELD CA
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The stability of the flapping motion of a single blade of a helicopter rotor is examined using the techniques of perturbation theory. The equation of motion studied is linear, with periodic aerodynamic coefficients due to the forward speed of the rotor. Blade pitch feedback proportional to both flapping displacement and flapping rate is included. Four cases are CONSIDERED small and large advance ratio, and small and large Lock number. The solution of this problem demonstrates the information which may be obtained using perturbation techniques.