Analysis of steady-state response regimes of a helicopter ground resonance model including a non-linear energy sink attachment |
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Institution: | 1. Department of Mechanical Engineering, Tarbiat Modares University, Tehran, Iran;2. Mechanical Rotary Equipment Department, Niroo Research Institute, Tehran, Iran;1. School of Mechanical Engineering and Automation, Northeastern University, Shenyang 110819, PR China;2. China North Vehicle Research Institute, Beijing 100072, PR China |
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Abstract: | 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 Non-linear 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 obtained using successively Coleman transformation and binormal transformation. A theoretical/numerical analysis of the steady-state responses of this model when a Non-linear Energy Sink is attached on the fuselage in an ungrounded configuration is performed. 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 Helicopter Ground Resonance. A systematic method based on simple analytical criterions is proposed to predict the steady-state response regimes. The method is finally validated numerically. |
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Keywords: | Helicopter ground resonance Passive control Non-linear energy sink Relaxation oscillations Strongly modulated response |
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