Abstract
The paper presents selected aspects of numerical analyses on the assessment of the helicopter’s main rotor operational stability, presents key issues for stability assessment, and discusses the application of the co-simulation methodology for helicopter’s main rotor exampled by a prototype unmanned aerial vehicle rotor. The presented approach enables the analysis and mapping of the rotor’s operation taking into account the effects of the aeroelasticity of the blade itself. The impact of wind on the tested structure is presented for two cases and thrust force for the cases of starting the rotor for front and crosswind was evaluated. The transition of the rotor between the idle and working revolutions at a small collective angle does not generate unstable states independently in the wind direction.
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