Analysis of steady-state response regimes of a helicopter ground resonance model including a nonlinear energy sink attachment
Résumé
Helicopter Ground Resonance is a dynamic instability involving the coupling of the blades motion in the rotational plane (i.e. the lag motion) and the motion of the fuselage. This paper presents a study of the capacity of a Nonlinear Energy Sink to control a Helicopter Ground Resonance. A model of helicopter with a minimum number of degrees of freedom that can reproduce Helicopter Ground Resonance instability is ob- tained using successively Coleman transformation and binormal transformation. A theoretical/numerical analysis of the steady- state responses of this model when a Nonlinear Energy Sink is attached on the fuselage in an ungrounded configuration is performed. The analytic approach is based on complexifcation-averaging
method together with geometric singular perturbation theory. Four steady-state responses are highlighted and explained analytically: complete suppression, partial suppression through strongly modulated response, partial suppression through periodic response and no suppression
of the Helicopter Ground Resonance. A systematic method based on simple analytical criterions is proposed to predict the steady-state response regimes. The method is fnally validated numerically
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