Analysis of steady-state response regimes of a helicopter ground resonance model including a nonlinear energy sink attachment
Résumé
Helicopter Ground Resonance (GR) 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 ability of a Nonlinear Energy Sink (NES) to control a GR. A model of helicopter having a minimum number of degrees of freedom and being able to reproduce GR instability is obtained using successively Coleman transformation and binormal transformation. A theoretical/numerical analysis of the steady-state responses of this model is performed when a NES is attached on the fuselage in an ungrounded configuration. The analytic approach is based on complexification-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 GR. A systematic method based on simple analytical criterions is proposed to predict these steady-state response regimes. The method is finally validated numerically.
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