헬리콥터 로터 소음 저감을 위한 능동거니플랩의 동해석 및 회전시험 시뮬레이션

Dynamic behavior of AGF(Active Gurney Flap) for BVI(Blade Vortex Interaction) noise reduction of a helicopter rotor system was investigated. In addition, in order to simulate the rotational test of the AGF, a model-scale rotor system was considered; which is 2-bladed hingeless rotor with 2.3m diameter and NACA23012 airfoil. The Gurney flap is a kind of small flat plate, mounted normal to the lower surface of the blade near to the trailing edge. An electric motor, L-shaped linkages and flap parts were integrated into a dummy blade. The AGF and rotor system was modeled using Midas-NFX; which is the commercial FEA code. The natural frequencies and mode shapes of a model-scale rotor system were calculated, then the dynamic displacement of the AGF with considering both the centrifugal force and active control input was investigated. The analysis results showed that the 4㎜ dynamic stroke requirement of the AGF