An approximate theoretical method is presented which determined the limit cycle behavior of a helicopter model which has one or two nonlinear dampers. The relationship during unstable ground resonance oscillations between lagging motion of the blades and fuselage motion is discussed. An experiment was carried out on using a helicopter scale model. The experimental results agree with those of the theoretical analysis.
Nonlinear Dynamics of a Helicopter Model in Ground Resonance
1985-11-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Nonlinear Analysis of Helicopter Ground Resonance
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