Abstract
The aim of this paper is to investigate the effectiveness of the nonlinear energy sink on the aeroelastic behaviors of rotor blades. For this purpose, a single hingeless helicopter rotor blade in a hover flight aerodynamic condition is considered. The performance of two linear vibration absorbers is investigated in this aeroelastic system, as well for comparison. The linear stability and nonlinear responses of the systems are analyzed and compared with the primary rotor blade system. The results show that both the linear and nonlinear vibration absorbers can delay the flutter point. The obtained results from the nonlinear analysis give helpful details of different systems.
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