In this paper, an analysis is developed to further study aerodynamics and structure dynamics of a helicopter rotor with embedded Continuous Trailing-Edge Flap (CTEF). A utility helicopter baseline rotor model is developed using Dymore multibody dynamics code. 2-D airfoil aero-structural coupled method is applied to obtain sectional characteristics. A Discrete Trailing-Edge Flap (DTEF) rotor model is built as well as a comparison case with CTEF rotor. Wind tunnel trim is used to adjust rotor pitch angle to achieve a targeting rotor thrust and zero first per rev blade flapping. CTEF rotor is analyzed with respect to varying advance ratios and comparison is made in terms of aerodynamics, structure dynamics and control authority with the baseline and DTEF rotor models.
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